DU 86-137/25 AIRFOIL (du861372-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: DU 86-137/25 AIRFOIL (du861372-il) Reynolds number: 500,000 Max Cl/Cd: 46.65 at α=7.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-du861372-il-500000.txt Download as CSV file: xf-du861372-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: DU 86-137/25 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-15.000 -0.4909 0.14319 0.13941 0.0008 0.2984 0.0137
-14.750 -0.4929 0.13904 0.13525 -0.0018 0.2985 0.0142
-14.500 -0.6000 0.13681 0.13261 -0.0104 0.2970 0.0131
-13.500 -0.6685 0.09295 0.08868 -0.0346 0.2964 0.0136
-13.250 -0.6979 0.08377 0.07936 -0.0408 0.2961 0.0133
-13.000 -0.7217 0.07731 0.07276 -0.0445 0.2963 0.0132
-12.750 -0.7435 0.07187 0.06720 -0.0467 0.2964 0.0133
-12.500 -0.7649 0.06726 0.06245 -0.0478 0.2963 0.0133
-12.250 -0.7824 0.06352 0.05857 -0.0479 0.2963 0.0133
-12.000 -0.7992 0.06007 0.05499 -0.0473 0.2966 0.0134
-11.750 -0.8147 0.05707 0.05184 -0.0459 0.2967 0.0135
-11.500 -0.8290 0.05440 0.04902 -0.0440 0.2968 0.0136
-11.250 -0.8432 0.05198 0.04643 -0.0415 0.2969 0.0139
-11.000 -0.8544 0.04994 0.04423 -0.0385 0.2970 0.0140
-10.750 -0.8675 0.04826 0.04238 -0.0344 0.2972 0.0142
-10.500 -0.8803 0.04729 0.04117 -0.0297 0.2974 0.0146
-10.250 -0.8951 0.04696 0.04045 -0.0245 0.2976 0.0148
-10.000 -0.9080 0.04710 0.04013 -0.0195 0.2979 0.0150
-9.750 -0.9160 0.04715 0.03965 -0.0150 0.2981 0.0150
-9.500 -0.9141 0.04657 0.03863 -0.0118 0.2986 0.0151
-9.250 -0.9078 0.04589 0.03749 -0.0092 0.2990 0.0151
-9.000 -0.8488 0.03662 0.02896 -0.0153 0.3000 0.0156
-8.750 -0.8254 0.03424 0.02654 -0.0154 0.3007 0.0159
-8.500 -0.8054 0.03257 0.02473 -0.0147 0.3013 0.0162
-8.250 -0.7856 0.03115 0.02316 -0.0140 0.3021 0.0165
-8.000 -0.7658 0.03000 0.02183 -0.0131 0.3026 0.0169
-7.750 -0.7468 0.02923 0.02086 -0.0120 0.3033 0.0173
-7.500 -0.7328 0.02941 0.02069 -0.0100 0.3038 0.0178
-7.250 -0.7210 0.03021 0.02103 -0.0075 0.3043 0.0180
-7.000 -0.7016 0.03047 0.02095 -0.0062 0.3049 0.0181
-6.750 -0.6614 0.02594 0.01681 -0.0089 0.3057 0.0185
-6.500 -0.6263 0.02384 0.01487 -0.0104 0.3067 0.0190
-6.250 -0.5982 0.02273 0.01375 -0.0108 0.3075 0.0196
-6.000 -0.5748 0.02223 0.01313 -0.0102 0.3084 0.0205
-5.750 -0.5620 0.02311 0.01359 -0.0078 0.3091 0.0211
-5.500 -0.5219 0.02058 0.01138 -0.0102 0.3100 0.0219
-5.250 -0.4921 0.01940 0.01034 -0.0108 0.3107 0.0232
-5.000 -0.4763 0.02013 0.01067 -0.0089 0.3113 0.0244
-4.750 -0.4446 0.01751 0.00857 -0.0100 0.3118 0.0268
-4.500 -0.4278 0.01643 0.00754 -0.0085 0.3122 0.0291
-4.250 -0.4109 0.01559 0.00675 -0.0070 0.3125 0.0306
-4.000 -0.3894 0.01513 0.00626 -0.0062 0.3128 0.0318
-3.750 -0.3702 0.01442 0.00555 -0.0050 0.3132 0.0334
-3.500 -0.3477 0.01397 0.00506 -0.0044 0.3137 0.0348
-3.250 -0.3230 0.01368 0.00472 -0.0040 0.3144 0.0358
-3.000 -0.2974 0.01348 0.00449 -0.0038 0.3150 0.0367
-2.750 -0.2714 0.01330 0.00429 -0.0036 0.3156 0.0378
-2.500 -0.2454 0.01312 0.00412 -0.0034 0.3162 0.0396
-2.250 -0.2197 0.01292 0.00397 -0.0033 0.3168 0.0517
-2.000 -0.1929 0.01284 0.00386 -0.0032 0.3171 0.0548
-1.750 -0.1662 0.01277 0.00379 -0.0032 0.3169 0.0562
-1.500 -0.1398 0.01272 0.00373 -0.0031 0.3165 0.0586
-1.250 -0.1133 0.01268 0.00369 -0.0031 0.3160 0.0603
-1.000 -0.0867 0.01265 0.00364 -0.0031 0.3157 0.0618
-0.750 -0.0602 0.01267 0.00362 -0.0030 0.3153 0.0600
-0.500 -0.0332 0.01266 0.00357 -0.0031 0.3154 0.0566
-0.250 -0.0063 0.01263 0.00351 -0.0031 0.3155 0.0542
0.000 0.0204 0.01261 0.00348 -0.0031 0.3155 0.0510
0.250 0.0477 0.01269 0.00347 -0.0031 0.3155 0.0349
0.500 0.0735 0.01272 0.00351 -0.0030 0.3150 0.0328
0.750 0.0989 0.01285 0.00363 -0.0028 0.3141 0.0316
1.000 0.1246 0.01300 0.00375 -0.0026 0.3134 0.0307
1.250 0.1505 0.01311 0.00384 -0.0025 0.3130 0.0313
1.500 0.1763 0.01320 0.00396 -0.0024 0.3125 0.0578
1.750 0.2026 0.01336 0.00410 -0.0024 0.3120 0.0590
2.000 0.2294 0.01341 0.00418 -0.0024 0.3114 0.0615
2.250 0.2558 0.01358 0.00438 -0.0024 0.3094 0.0655
2.500 0.2826 0.01466 0.00536 -0.0028 0.3044 0.1293
2.750 0.3095 0.01548 0.00625 -0.0031 0.2961 0.1623
3.000 0.3228 0.01412 0.00652 -0.0019 0.2861 0.6479
3.250 0.3468 0.01529 0.00795 -0.0016 0.2722 0.7204
3.500 0.3705 0.01557 0.00846 -0.0007 0.2636 0.7602
3.750 0.3951 0.01614 0.00916 0.0000 0.2580 0.7822
4.000 0.4166 0.01662 0.00983 0.0018 0.2523 0.8066
4.250 0.4402 0.01687 0.01019 0.0026 0.2461 0.8144
4.500 0.4656 0.01682 0.01024 0.0030 0.2405 0.8195
4.750 0.4894 0.01696 0.01046 0.0035 0.2371 0.8227
5.000 0.5142 0.01638 0.01006 0.0040 0.2298 0.8248
5.250 0.5370 0.01589 0.00975 0.0049 0.2241 0.8272
5.500 0.5680 0.01561 0.00953 0.0043 0.1899 0.8294
5.750 0.5956 0.01408 0.00812 0.0047 0.1686 0.8323
6.000 0.6256 0.01389 0.00783 0.0042 0.1444 0.8346
6.250 0.6492 0.01424 0.00807 0.0045 0.1204 0.8367
6.500 0.6703 0.01465 0.00829 0.0053 0.0961 0.8388
6.750 0.6917 0.01505 0.00860 0.0060 0.0799 0.8411
7.000 0.7135 0.01545 0.00895 0.0067 0.0679 0.8435
7.250 0.7359 0.01581 0.00929 0.0073 0.0589 0.8460
7.500 0.7571 0.01626 0.00971 0.0081 0.0510 0.8484
7.750 0.7786 0.01669 0.01011 0.0088 0.0452 0.8509
8.000 0.7979 0.01723 0.01068 0.0098 0.0405 0.8535
8.250 0.8179 0.01761 0.01110 0.0108 0.0372 0.8560
8.500 0.8334 0.01822 0.01172 0.0124 0.0338 0.8587
8.750 0.8479 0.01883 0.01242 0.0142 0.0316 0.8616
9.000 0.8654 0.01930 0.01294 0.0155 0.0301 0.8646
9.250 0.8797 0.01981 0.01350 0.0173 0.0284 0.8679
9.500 0.8921 0.02041 0.01413 0.0194 0.0274 0.8711
9.750 0.8992 0.02122 0.01501 0.0221 0.0261 0.8747
10.000 0.8963 0.02267 0.01657 0.0258 0.0251 0.8792
10.250 0.9116 0.02335 0.01733 0.0270 0.0245 0.8829
10.500 0.9279 0.02403 0.01808 0.0280 0.0236 0.8866
10.750 0.9412 0.02480 0.01896 0.0295 0.0229 0.8909
11.000 0.9547 0.02563 0.01988 0.0307 0.0221 0.8956
11.250 0.9677 0.02658 0.02090 0.0320 0.0214 0.9004
11.500 0.9807 0.02747 0.02185 0.0331 0.0207 0.9056
11.750 0.9911 0.02858 0.02305 0.0345 0.0201 0.9122
12.000 0.9964 0.03054 0.02514 0.0362 0.0193 0.9202
12.250 1.0062 0.03243 0.02725 0.0374 0.0189 0.9308
12.500 1.0256 0.03345 0.02845 0.0369 0.0185 0.9477
12.750 1.0487 0.03486 0.03004 0.0352 0.0178 1.0000
13.000 1.0598 0.03637 0.03168 0.0356 0.0173 1.0000
13.250 1.0687 0.03804 0.03346 0.0361 0.0168 1.0000
13.500 1.0750 0.03993 0.03547 0.0366 0.0164 1.0000
13.750 1.0795 0.04195 0.03761 0.0372 0.0161 1.0000
14.000 1.0833 0.04393 0.03969 0.0376 0.0158 1.0000
14.250 1.0834 0.04634 0.04222 0.0381 0.0155 1.0000
14.500 1.0836 0.04868 0.04464 0.0383 0.0152 1.0000
14.750 1.0774 0.05193 0.04805 0.0384 0.0151 1.0000
15.000 1.0700 0.05532 0.05155 0.0382 0.0149 1.0000
15.250 1.0564 0.05970 0.05611 0.0375 0.0148 1.0000
15.500 1.0398 0.06470 0.06130 0.0361 0.0147 1.0000
15.750 1.0169 0.07111 0.06791 0.0336 0.0146 1.0000
16.000 0.9948 0.07824 0.07523 0.0300 0.0146 1.0000
16.250 0.9708 0.08676 0.08395 0.0249 0.0146 1.0000
16.500 0.9493 0.09621 0.09358 0.0185 0.0148 1.0000
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