RG 15A-1.8/11.0 AIRFOIL (rg15a111-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: RG 15A-1.8/11.0 AIRFOIL (rg15a111-il) Reynolds number: 1,000,000 Max Cl/Cd: 101.87 at α=5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-rg15a111-il-1000000.txt Download as CSV file: xf-rg15a111-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: RG 15A-1.8/11.0 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
------ -------- --------- --------- -------- -------- --------
-13.750 -0.8747 0.05598 0.05351 -0.0562 1.0000 0.0066
-13.500 -0.8942 0.04836 0.04572 -0.0622 1.0000 0.0066
-13.250 -0.9094 0.04287 0.04010 -0.0660 1.0000 0.0067
-13.000 -0.9248 0.03839 0.03545 -0.0680 1.0000 0.0067
-12.750 -0.9359 0.03518 0.03210 -0.0683 1.0000 0.0068
-12.500 -0.9418 0.03312 0.02995 -0.0672 1.0000 0.0068
-12.250 -0.9572 0.03113 0.02783 -0.0639 1.0000 0.0069
-12.000 -0.9640 0.02999 0.02661 -0.0599 1.0000 0.0069
-11.750 -0.9614 0.02878 0.02531 -0.0573 1.0000 0.0071
-11.500 -0.9546 0.02780 0.02426 -0.0549 1.0000 0.0072
-11.250 -0.9496 0.02648 0.02281 -0.0524 1.0000 0.0073
-11.000 -0.9426 0.02520 0.02139 -0.0499 1.0000 0.0074
-10.750 -0.9308 0.02435 0.02045 -0.0479 1.0000 0.0076
-10.500 -0.9199 0.02331 0.01928 -0.0457 1.0000 0.0078
-10.250 -0.9094 0.02211 0.01794 -0.0434 1.0000 0.0079
-10.000 -0.8966 0.02112 0.01683 -0.0414 1.0000 0.0081
-9.750 -0.8729 0.02012 0.01571 -0.0415 0.9992 0.0083
-9.500 -0.8424 0.01916 0.01462 -0.0428 0.9977 0.0086
-9.250 -0.8106 0.01845 0.01380 -0.0442 0.9962 0.0088
-9.000 -0.7827 0.01652 0.01166 -0.0456 0.9946 0.0094
-8.750 -0.7519 0.01581 0.01091 -0.0468 0.9930 0.0099
-8.500 -0.7212 0.01530 0.01036 -0.0478 0.9908 0.0104
-8.250 -0.6892 0.01485 0.00986 -0.0490 0.9888 0.0110
-8.000 -0.6562 0.01440 0.00936 -0.0503 0.9870 0.0116
-7.750 -0.6222 0.01403 0.00893 -0.0518 0.9856 0.0120
-7.500 -0.5910 0.01270 0.00749 -0.0533 0.9841 0.0131
-7.250 -0.5563 0.01222 0.00698 -0.0550 0.9831 0.0140
-7.000 -0.5299 0.01176 0.00650 -0.0548 0.9784 0.0148
-6.750 -0.4974 0.01137 0.00606 -0.0560 0.9758 0.0156
-6.500 -0.4639 0.01079 0.00541 -0.0574 0.9738 0.0167
-6.250 -0.4295 0.01026 0.00486 -0.0590 0.9721 0.0185
-6.000 -0.3936 0.00987 0.00445 -0.0608 0.9709 0.0199
-5.750 -0.3658 0.00956 0.00410 -0.0608 0.9653 0.0209
-5.500 -0.3342 0.00909 0.00361 -0.0616 0.9612 0.0241
-5.250 -0.3005 0.00876 0.00327 -0.0629 0.9579 0.0272
-5.000 -0.2724 0.00832 0.00293 -0.0630 0.9508 0.0431
-4.750 -0.2406 0.00794 0.00264 -0.0639 0.9448 0.0654
-4.250 -0.1794 0.00740 0.00221 -0.0652 0.9282 0.1029
-4.000 -0.1513 0.00717 0.00203 -0.0652 0.9165 0.1250
-3.750 -0.1237 0.00693 0.00186 -0.0652 0.9043 0.1553
-3.500 -0.0967 0.00668 0.00171 -0.0650 0.8914 0.1934
-3.250 -0.0699 0.00646 0.00158 -0.0648 0.8783 0.2311
-3.000 -0.0433 0.00626 0.00145 -0.0646 0.8649 0.2713
-2.750 -0.0174 0.00600 0.00134 -0.0643 0.8511 0.3303
-2.500 0.0082 0.00571 0.00124 -0.0639 0.8372 0.4017
-2.250 0.0343 0.00551 0.00115 -0.0635 0.8230 0.4564
-2.000 0.0602 0.00532 0.00108 -0.0632 0.8084 0.5144
-1.750 0.0861 0.00515 0.00106 -0.0627 0.7938 0.5782
-1.500 0.1125 0.00508 0.00105 -0.0623 0.7791 0.6255
-1.250 0.1394 0.00508 0.00105 -0.0620 0.7642 0.6512
-1.000 0.1665 0.00510 0.00105 -0.0617 0.7493 0.6698
-0.750 0.1936 0.00513 0.00105 -0.0614 0.7340 0.6847
-0.500 0.2208 0.00517 0.00105 -0.0612 0.7186 0.6975
-0.250 0.2479 0.00522 0.00106 -0.0609 0.7026 0.7094
0.000 0.2750 0.00528 0.00108 -0.0606 0.6862 0.7207
0.250 0.3020 0.00533 0.00110 -0.0603 0.6691 0.7312
0.500 0.3290 0.00540 0.00112 -0.0600 0.6517 0.7407
0.750 0.3559 0.00548 0.00115 -0.0598 0.6335 0.7502
1.000 0.3826 0.00556 0.00119 -0.0594 0.6149 0.7596
1.250 0.4094 0.00564 0.00123 -0.0592 0.5951 0.7684
1.500 0.4361 0.00575 0.00128 -0.0589 0.5751 0.7778
1.750 0.4626 0.00585 0.00134 -0.0585 0.5549 0.7872
2.000 0.4891 0.00596 0.00141 -0.0582 0.5335 0.7968
2.250 0.5154 0.00609 0.00148 -0.0578 0.5124 0.8070
2.500 0.5416 0.00620 0.00157 -0.0574 0.4909 0.8171
2.750 0.5676 0.00634 0.00166 -0.0570 0.4690 0.8277
3.000 0.5937 0.00648 0.00175 -0.0566 0.4469 0.8393
3.250 0.6189 0.00664 0.00186 -0.0561 0.4222 0.8518
3.500 0.6441 0.00680 0.00198 -0.0555 0.3978 0.8646
3.750 0.6693 0.00695 0.00210 -0.0549 0.3775 0.8777
4.000 0.6941 0.00710 0.00223 -0.0543 0.3565 0.8923
4.250 0.7179 0.00728 0.00237 -0.0534 0.3346 0.9097
4.500 0.7407 0.00742 0.00251 -0.0523 0.3147 0.9317
4.750 0.7658 0.00758 0.00265 -0.0517 0.2947 0.9605
5.000 0.8007 0.00786 0.00284 -0.0534 0.2676 0.9875
5.250 0.8293 0.00818 0.00303 -0.0538 0.2410 1.0000
5.500 0.8537 0.00850 0.00324 -0.0533 0.2167 1.0000
5.750 0.8784 0.00881 0.00345 -0.0529 0.1954 1.0000
6.250 0.9274 0.00945 0.00394 -0.0519 0.1576 1.0000
6.500 0.9515 0.00981 0.00420 -0.0513 0.1390 1.0000
6.750 0.9755 0.01017 0.00448 -0.0507 0.1228 1.0000
7.000 0.9993 0.01054 0.00479 -0.0501 0.1077 1.0000
7.250 1.0230 0.01092 0.00510 -0.0495 0.0938 1.0000
7.500 1.0465 0.01130 0.00542 -0.0489 0.0819 1.0000
7.750 1.0699 0.01168 0.00576 -0.0482 0.0717 1.0000
8.000 1.0930 0.01207 0.00613 -0.0475 0.0617 1.0000
8.250 1.1157 0.01250 0.00651 -0.0468 0.0517 1.0000
8.500 1.1380 0.01294 0.00691 -0.0460 0.0434 1.0000
8.750 1.1596 0.01344 0.00736 -0.0450 0.0364 1.0000
9.000 1.1820 0.01384 0.00777 -0.0442 0.0326 1.0000
9.250 1.2028 0.01437 0.00829 -0.0432 0.0283 1.0000
9.500 1.2252 0.01473 0.00869 -0.0424 0.0263 1.0000
9.750 1.2457 0.01524 0.00919 -0.0414 0.0237 1.0000
10.000 1.2656 0.01577 0.00974 -0.0402 0.0214 1.0000
10.250 1.2869 0.01615 0.01017 -0.0393 0.0199 1.0000
10.500 1.3061 0.01668 0.01070 -0.0381 0.0179 1.0000
10.750 1.3241 0.01725 0.01132 -0.0366 0.0160 1.0000
11.000 1.3429 0.01773 0.01181 -0.0354 0.0141 1.0000
11.250 1.3563 0.01842 0.01252 -0.0332 0.0121 1.0000
11.500 1.3711 0.01895 0.01310 -0.0312 0.0109 1.0000
11.750 1.3811 0.01976 0.01392 -0.0286 0.0094 1.0000
12.000 1.3929 0.02047 0.01470 -0.0263 0.0085 1.0000
12.250 1.4051 0.02116 0.01545 -0.0242 0.0079 1.0000
12.500 1.4144 0.02204 0.01637 -0.0219 0.0073 1.0000
12.750 1.4171 0.02335 0.01778 -0.0189 0.0066 1.0000
13.000 1.4260 0.02430 0.01881 -0.0168 0.0064 1.0000
13.250 1.4353 0.02525 0.01984 -0.0149 0.0061 1.0000
13.500 1.4412 0.02648 0.02116 -0.0129 0.0059 1.0000
13.750 1.4471 0.02777 0.02253 -0.0110 0.0056 1.0000
14.000 1.4516 0.02922 0.02407 -0.0093 0.0054 1.0000
14.250 1.4546 0.03089 0.02582 -0.0078 0.0053 1.0000
14.500 1.4553 0.03285 0.02788 -0.0064 0.0051 1.0000
14.750 1.4522 0.03529 0.03043 -0.0052 0.0050 1.0000
15.000 1.4437 0.03845 0.03372 -0.0043 0.0048 1.0000
15.250 1.4294 0.04252 0.03795 -0.0041 0.0046 1.0000
15.500 1.4216 0.04617 0.04173 -0.0043 0.0045 1.0000
15.750 1.4151 0.04994 0.04563 -0.0050 0.0045 1.0000
16.000 1.4066 0.05419 0.05001 -0.0062 0.0045 1.0000
16.250 1.3987 0.05861 0.05456 -0.0077 0.0045 1.0000
16.500 1.3863 0.06397 0.06005 -0.0099 0.0045 1.0000
16.750 1.3779 0.06896 0.06516 -0.0121 0.0044 1.0000
17.000 1.3584 0.07600 0.07236 -0.0155 0.0045 1.0000
17.250 1.3469 0.08198 0.07846 -0.0185 0.0044 1.0000
17.500 1.3238 0.09022 0.08686 -0.0228 0.0044 1.0000
17.750 1.3092 0.09723 0.09399 -0.0265 0.0044 1.0000
18.000 1.2909 0.10506 0.10195 -0.0308 0.0044 1.0000
18.250 1.2691 0.11382 0.11084 -0.0357 0.0044 1.0000
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Polar data table (+)
Polar graphs
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