RAF 31 AIRFOIL (raf31-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: RAF 31 AIRFOIL (raf31-il) Reynolds number: 1,000,000 Max Cl/Cd: 106.31 at α=4.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-raf31-il-1000000.txt Download as CSV file: xf-raf31-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: RAF 31 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-17.500 -0.8513 0.11092 0.10873 -0.0361 1.0000 0.0158
-17.250 -0.9059 0.09604 0.09363 -0.0447 1.0000 0.0158
-17.000 -0.9326 0.08718 0.08466 -0.0499 1.0000 0.0159
-16.750 -0.9651 0.07771 0.07503 -0.0556 1.0000 0.0159
-16.500 -0.9854 0.07081 0.06801 -0.0598 1.0000 0.0159
-16.250 -1.0010 0.06489 0.06199 -0.0634 1.0000 0.0160
-16.000 -1.0133 0.05961 0.05661 -0.0666 1.0000 0.0161
-15.750 -1.0223 0.05489 0.05180 -0.0695 1.0000 0.0162
-15.500 -1.0257 0.05108 0.04793 -0.0719 1.0000 0.0163
-15.250 -1.0311 0.04716 0.04390 -0.0742 1.0000 0.0164
-15.000 -1.0332 0.04386 0.04052 -0.0761 1.0000 0.0166
-14.750 -1.0327 0.04106 0.03765 -0.0775 1.0000 0.0167
-14.500 -1.0348 0.03818 0.03467 -0.0787 1.0000 0.0169
-14.250 -1.0340 0.03587 0.03227 -0.0793 1.0000 0.0171
-14.000 -1.0292 0.03425 0.03059 -0.0794 1.0000 0.0174
-13.750 -1.0295 0.03236 0.02859 -0.0790 1.0000 0.0176
-13.500 -1.0264 0.03108 0.02725 -0.0779 1.0000 0.0179
-13.250 -1.0321 0.02928 0.02532 -0.0756 1.0000 0.0180
-13.000 -1.0308 0.02849 0.02446 -0.0728 1.0000 0.0182
-12.750 -1.0317 0.02796 0.02386 -0.0690 1.0000 0.0185
-12.500 -1.0301 0.02733 0.02314 -0.0653 1.0000 0.0187
-12.250 -1.0223 0.02678 0.02251 -0.0626 1.0000 0.0189
-12.000 -1.0139 0.02628 0.02193 -0.0599 1.0000 0.0191
-11.750 -1.0187 0.02392 0.01943 -0.0560 0.9998 0.0196
-11.500 -0.9899 0.02288 0.01836 -0.0576 0.9982 0.0200
-11.250 -0.9587 0.02229 0.01775 -0.0593 0.9962 0.0205
-11.000 -0.9275 0.02160 0.01700 -0.0610 0.9942 0.0210
-10.750 -0.8987 0.02099 0.01633 -0.0620 0.9913 0.0215
-10.500 -0.8690 0.02034 0.01561 -0.0631 0.9880 0.0221
-10.250 -0.8384 0.01959 0.01479 -0.0644 0.9852 0.0226
-10.000 -0.8077 0.01908 0.01420 -0.0656 0.9821 0.0230
-9.750 -0.7802 0.01869 0.01373 -0.0659 0.9757 0.0233
-9.500 -0.7544 0.01703 0.01197 -0.0667 0.9716 0.0241
-9.250 -0.7307 0.01608 0.01100 -0.0665 0.9631 0.0246
-9.000 -0.6983 0.01538 0.01027 -0.0680 0.9589 0.0252
-8.750 -0.6649 0.01473 0.00959 -0.0697 0.9528 0.0257
-8.500 -0.6262 0.01417 0.00898 -0.0725 0.9477 0.0264
-8.250 -0.5872 0.01361 0.00836 -0.0753 0.9417 0.0272
-8.000 -0.5512 0.01306 0.00774 -0.0774 0.9341 0.0276
-7.750 -0.5178 0.01260 0.00722 -0.0789 0.9258 0.0281
-7.500 -0.4877 0.01226 0.00679 -0.0796 0.9162 0.0284
-7.250 -0.4628 0.01187 0.00632 -0.0792 0.9070 0.0288
-7.000 -0.4409 0.01124 0.00558 -0.0783 0.8987 0.0296
-6.750 -0.4190 0.01082 0.00512 -0.0772 0.8906 0.0301
-6.500 -0.3948 0.01050 0.00472 -0.0766 0.8838 0.0308
-6.250 -0.3713 0.01020 0.00439 -0.0757 0.8771 0.0314
-6.000 -0.3467 0.00996 0.00409 -0.0751 0.8703 0.0321
-5.750 -0.3221 0.00972 0.00381 -0.0744 0.8636 0.0328
-5.500 -0.2973 0.00951 0.00355 -0.0738 0.8563 0.0336
-5.250 -0.2720 0.00932 0.00332 -0.0732 0.8493 0.0343
-5.000 -0.2468 0.00914 0.00310 -0.0726 0.8411 0.0347
-4.750 -0.2221 0.00892 0.00283 -0.0719 0.8325 0.0364
-4.500 -0.1970 0.00873 0.00261 -0.0713 0.8234 0.0385
-4.250 -0.1718 0.00855 0.00241 -0.0707 0.8143 0.0414
-4.000 -0.1481 0.00825 0.00222 -0.0698 0.8046 0.0689
-3.750 -0.1227 0.00808 0.00208 -0.0693 0.7951 0.0841
-3.500 -0.0974 0.00792 0.00194 -0.0688 0.7863 0.0982
-3.250 -0.0727 0.00770 0.00179 -0.0681 0.7767 0.1229
-3.000 -0.0495 0.00734 0.00164 -0.0673 0.7680 0.1829
-2.750 -0.0250 0.00712 0.00152 -0.0666 0.7594 0.2215
-2.500 -0.0007 0.00687 0.00142 -0.0659 0.7506 0.2697
-2.250 0.0236 0.00669 0.00135 -0.0652 0.7414 0.3169
-2.000 0.0494 0.00655 0.00130 -0.0648 0.7334 0.3511
-1.750 0.0750 0.00645 0.00126 -0.0643 0.7263 0.3817
-1.500 0.1014 0.00636 0.00123 -0.0639 0.7196 0.4068
-1.250 0.1272 0.00626 0.00120 -0.0635 0.7127 0.4362
-1.000 0.1530 0.00615 0.00118 -0.0630 0.7064 0.4682
-0.750 0.1787 0.00605 0.00117 -0.0625 0.6993 0.5033
-0.500 0.2043 0.00598 0.00117 -0.0620 0.6923 0.5356
-0.250 0.2302 0.00590 0.00118 -0.0615 0.6849 0.5690
0.000 0.2558 0.00587 0.00119 -0.0609 0.6776 0.5978
0.250 0.2823 0.00582 0.00120 -0.0605 0.6703 0.6189
0.500 0.3081 0.00580 0.00122 -0.0600 0.6630 0.6404
0.750 0.3345 0.00577 0.00124 -0.0596 0.6556 0.6612
1.250 0.3854 0.00572 0.00130 -0.0584 0.6377 0.7130
1.500 0.4101 0.00570 0.00135 -0.0576 0.6284 0.7418
1.750 0.4342 0.00570 0.00139 -0.0566 0.6141 0.7690
2.000 0.4582 0.00572 0.00143 -0.0557 0.5961 0.7929
2.250 0.4815 0.00577 0.00148 -0.0546 0.5728 0.8155
2.500 0.5039 0.00585 0.00154 -0.0533 0.5441 0.8391
2.750 0.5248 0.00600 0.00163 -0.0518 0.5065 0.8669
3.000 0.5493 0.00617 0.00177 -0.0510 0.4727 0.9036
3.500 0.6488 0.00668 0.00216 -0.0610 0.4272 0.9582
3.750 0.6890 0.00687 0.00231 -0.0637 0.4136 0.9731
4.000 0.7225 0.00705 0.00245 -0.0650 0.4001 0.9855
4.250 0.7579 0.00725 0.00260 -0.0667 0.3834 0.9931
4.500 0.7952 0.00748 0.00274 -0.0690 0.3561 0.9980
4.750 0.8208 0.00806 0.00297 -0.0690 0.2858 1.0000
5.000 0.8383 0.00841 0.00320 -0.0669 0.2635 1.0000
5.250 0.8574 0.00869 0.00341 -0.0652 0.2469 1.0000
5.500 0.8764 0.00898 0.00362 -0.0635 0.2259 1.0000
5.750 0.8899 0.00958 0.00391 -0.0608 0.1667 1.0000
6.000 0.9036 0.01017 0.00429 -0.0581 0.1285 1.0000
6.250 0.9214 0.01055 0.00458 -0.0562 0.1106 1.0000
6.500 0.9404 0.01088 0.00485 -0.0545 0.0995 1.0000
6.750 0.9606 0.01114 0.00510 -0.0530 0.0918 1.0000
7.000 0.9798 0.01147 0.00537 -0.0514 0.0838 1.0000
7.250 1.0006 0.01170 0.00561 -0.0501 0.0800 1.0000
7.500 1.0199 0.01201 0.00589 -0.0485 0.0747 1.0000
7.750 1.0399 0.01227 0.00616 -0.0470 0.0708 1.0000
8.000 1.0599 0.01253 0.00642 -0.0456 0.0669 1.0000
8.250 1.0783 0.01287 0.00672 -0.0439 0.0623 1.0000
8.500 1.0980 0.01313 0.00700 -0.0424 0.0594 1.0000
8.750 1.1165 0.01342 0.00729 -0.0407 0.0561 1.0000
9.000 1.1315 0.01377 0.00762 -0.0384 0.0515 1.0000
9.250 1.1485 0.01405 0.00790 -0.0364 0.0474 1.0000
9.500 1.1624 0.01448 0.00829 -0.0340 0.0390 1.0000
9.750 1.1724 0.01515 0.00884 -0.0310 0.0261 1.0000
10.000 1.1834 0.01582 0.00946 -0.0283 0.0206 1.0000
10.250 1.1973 0.01638 0.01004 -0.0262 0.0186 1.0000
10.500 1.2103 0.01701 0.01070 -0.0240 0.0173 1.0000
10.750 1.2229 0.01770 0.01142 -0.0218 0.0161 1.0000
11.000 1.2374 0.01829 0.01207 -0.0200 0.0155 1.0000
11.250 1.2511 0.01897 0.01279 -0.0182 0.0150 1.0000
11.500 1.2644 0.01968 0.01355 -0.0165 0.0145 1.0000
11.750 1.2759 0.02054 0.01445 -0.0146 0.0139 1.0000
12.000 1.2816 0.02183 0.01581 -0.0122 0.0130 1.0000
12.250 1.2946 0.02265 0.01669 -0.0108 0.0128 1.0000
12.500 1.3069 0.02354 0.01764 -0.0094 0.0125 1.0000
12.750 1.3176 0.02458 0.01874 -0.0079 0.0122 1.0000
13.000 1.3284 0.02564 0.01986 -0.0065 0.0118 1.0000
13.250 1.3367 0.02691 0.02120 -0.0050 0.0116 1.0000
13.500 1.3451 0.02821 0.02257 -0.0037 0.0114 1.0000
13.750 1.3529 0.02961 0.02402 -0.0024 0.0111 1.0000
14.000 1.3553 0.03149 0.02597 -0.0010 0.0107 1.0000
14.250 1.3518 0.03397 0.02855 0.0005 0.0104 1.0000
14.500 1.3505 0.03635 0.03103 0.0016 0.0103 1.0000
14.750 1.3554 0.03825 0.03301 0.0023 0.0102 1.0000
15.000 1.3653 0.03972 0.03455 0.0028 0.0100 1.0000
15.250 1.3651 0.04220 0.03713 0.0034 0.0100 1.0000
15.500 1.3654 0.04473 0.03975 0.0038 0.0099 1.0000
15.750 1.3667 0.04727 0.04239 0.0040 0.0097 1.0000
16.000 1.3666 0.05004 0.04525 0.0041 0.0096 1.0000
16.250 1.3686 0.05264 0.04794 0.0040 0.0093 1.0000
16.500 1.3637 0.05616 0.05156 0.0036 0.0093 1.0000
16.750 1.3625 0.05936 0.05485 0.0031 0.0091 1.0000
17.000 1.3588 0.06296 0.05854 0.0024 0.0090 1.0000
17.250 1.3533 0.06690 0.06257 0.0015 0.0089 1.0000
17.500 1.3456 0.07129 0.06707 0.0002 0.0089 1.0000
17.750 1.3390 0.07564 0.07152 -0.0012 0.0088 1.0000
18.000 1.3334 0.07994 0.07590 -0.0027 0.0086 1.0000
18.250 1.3232 0.08496 0.08102 -0.0044 0.0086 1.0000
18.500 1.3146 0.08984 0.08599 -0.0063 0.0085 1.0000
18.750 1.3000 0.09570 0.09195 -0.0086 0.0084 1.0000
19.000 1.2890 0.10107 0.09742 -0.0108 0.0084 1.0000
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