AH 82-150 A (ah82150a-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: AH 82-150 A (ah82150a-il) Reynolds number: 100,000 Max Cl/Cd: 41.88 at α=8.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-ah82150a-il-100000-n5.txt Download as CSV file: xf-ah82150a-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: AH 82-150 A
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.750 -0.2900 0.08993 0.08514 -0.0869 0.9498 0.0301
-10.500 -0.2878 0.08274 0.07794 -0.0937 0.9437 0.0299
-10.250 -0.2937 0.07333 0.06849 -0.1029 0.9351 0.0297
-10.000 -0.3076 0.06463 0.05963 -0.1115 0.9260 0.0295
-9.750 -0.3229 0.05884 0.05364 -0.1158 0.9153 0.0293
-9.500 -0.3402 0.05470 0.04930 -0.1167 0.9039 0.0295
-9.250 -0.3565 0.05150 0.04585 -0.1154 0.8943 0.0298
-9.000 -0.3673 0.04808 0.04206 -0.1139 0.8862 0.0304
-8.750 -0.3744 0.04506 0.03860 -0.1117 0.8783 0.0311
-8.500 -0.3743 0.04210 0.03511 -0.1099 0.8722 0.0318
-8.250 -0.3700 0.03930 0.03191 -0.1082 0.8666 0.0324
-8.000 -0.3596 0.03704 0.02941 -0.1069 0.8613 0.0332
-7.750 -0.3434 0.03513 0.02724 -0.1062 0.8573 0.0342
-7.500 -0.3270 0.03379 0.02569 -0.1052 0.8527 0.0360
-7.250 -0.3106 0.03256 0.02419 -0.1041 0.8478 0.0385
-7.000 -0.2900 0.03089 0.02210 -0.1033 0.8442 0.0407
-6.750 -0.2657 0.02933 0.02011 -0.1028 0.8415 0.0423
-6.500 -0.2468 0.02793 0.01867 -0.1019 0.8369 0.0446
-6.250 -0.2257 0.02718 0.01785 -0.1012 0.8327 0.0479
-6.000 -0.2008 0.02622 0.01669 -0.1008 0.8295 0.0513
-5.750 -0.1741 0.02527 0.01554 -0.1006 0.8271 0.0540
-5.500 -0.1555 0.02451 0.01483 -0.0994 0.8229 0.0578
-5.250 -0.1355 0.02400 0.01427 -0.0984 0.8186 0.0625
-5.000 -0.1126 0.02338 0.01354 -0.0977 0.8154 0.0665
-4.750 -0.0897 0.02268 0.01283 -0.0971 0.8128 0.0714
-4.500 -0.0713 0.02239 0.01250 -0.0958 0.8087 0.0793
-4.250 -0.0536 0.02202 0.01216 -0.0944 0.8043 0.0876
-4.000 -0.0318 0.02158 0.01169 -0.0936 0.8010 0.1002
-3.750 -0.0089 0.02101 0.01128 -0.0931 0.7985 0.1327
-3.500 0.0059 0.02039 0.01113 -0.0915 0.7945 0.2222
-3.250 0.0150 0.01944 0.01098 -0.0894 0.7895 0.3937
-3.000 0.0229 0.01978 0.01245 -0.0831 0.7863 0.6442
-2.750 0.0491 0.02013 0.01258 -0.0827 0.7839 0.7054
-2.500 0.0662 0.02077 0.01312 -0.0801 0.7799 0.7349
-2.250 0.0776 0.02160 0.01393 -0.0758 0.7749 0.7635
-2.000 0.0924 0.02230 0.01460 -0.0714 0.7718 0.7913
-1.750 0.1111 0.02271 0.01490 -0.0681 0.7695 0.8146
-1.500 0.1241 0.02306 0.01520 -0.0647 0.7650 0.8280
-1.250 0.1381 0.02328 0.01536 -0.0621 0.7600 0.8362
-1.000 0.1628 0.02322 0.01517 -0.0619 0.7571 0.8409
-0.750 0.1915 0.02308 0.01488 -0.0626 0.7549 0.8445
-0.500 0.2053 0.02329 0.01504 -0.0606 0.7495 0.8475
-0.250 0.2241 0.02340 0.01508 -0.0595 0.7448 0.8506
0.000 0.2521 0.02331 0.01490 -0.0599 0.7421 0.8531
0.250 0.2837 0.02317 0.01465 -0.0609 0.7400 0.8554
0.500 0.2923 0.02358 0.01505 -0.0587 0.7328 0.8589
0.750 0.3174 0.02358 0.01499 -0.0585 0.7291 0.8607
1.000 0.3481 0.02345 0.01480 -0.0593 0.7267 0.8624
1.250 0.3819 0.02326 0.01456 -0.0605 0.7248 0.8639
1.500 0.3853 0.02384 0.01517 -0.0574 0.7158 0.8671
1.750 0.4166 0.02373 0.01502 -0.0583 0.7130 0.8690
2.000 0.4517 0.02352 0.01476 -0.0598 0.7110 0.8707
2.250 0.4575 0.02411 0.01540 -0.0571 0.7020 0.8737
2.500 0.4884 0.02396 0.01525 -0.0578 0.6989 0.8750
2.750 0.5235 0.02371 0.01498 -0.0591 0.6968 0.8762
3.000 0.5278 0.02433 0.01566 -0.0560 0.6875 0.8798
3.250 0.5603 0.02415 0.01549 -0.0570 0.6844 0.8817
3.500 0.5971 0.02386 0.01523 -0.0586 0.6823 0.8832
3.750 0.6019 0.02457 0.01601 -0.0559 0.6724 0.8865
4.000 0.6364 0.02432 0.01579 -0.0571 0.6696 0.8879
4.250 0.6699 0.02408 0.01562 -0.0581 0.6667 0.8895
4.500 0.6728 0.02469 0.01632 -0.0547 0.6568 0.8934
4.750 0.7104 0.02433 0.01602 -0.0563 0.6543 0.8954
5.250 0.7497 0.02467 0.01653 -0.0545 0.6408 0.9017
5.750 0.7898 0.02493 0.01701 -0.0526 0.6271 0.9081
6.250 0.8335 0.02516 0.01747 -0.0515 0.6131 0.9158
6.750 0.8778 0.02525 0.01785 -0.0501 0.5985 0.9255
7.250 0.9279 0.02512 0.01802 -0.0496 0.5830 0.9367
7.500 0.9418 0.02569 0.01879 -0.0484 0.5714 0.9464
7.750 0.9656 0.02590 0.01917 -0.0484 0.5610 0.9583
8.250 1.0276 0.02527 0.01888 -0.0496 0.5399 1.0000
8.500 1.0437 0.02535 0.01899 -0.0482 0.5129 1.0000
8.750 1.0588 0.02528 0.01874 -0.0463 0.4652 1.0000
9.000 1.0686 0.02592 0.01902 -0.0442 0.4083 1.0000
9.250 1.0679 0.02750 0.02020 -0.0416 0.3467 1.0000
9.500 1.0621 0.02966 0.02193 -0.0390 0.2820 1.0000
9.750 1.0532 0.03226 0.02406 -0.0365 0.2124 1.0000
10.000 1.0429 0.03521 0.02649 -0.0342 0.1406 1.0000
10.500 1.0311 0.04095 0.03146 -0.0307 0.0455 1.0000
10.750 1.0334 0.04327 0.03373 -0.0296 0.0353 1.0000
11.000 1.0364 0.04560 0.03607 -0.0287 0.0313 1.0000
11.250 1.0422 0.04772 0.03838 -0.0279 0.0291 1.0000
11.500 1.0463 0.05003 0.04084 -0.0273 0.0273 1.0000
11.750 1.0495 0.05250 0.04343 -0.0267 0.0259 1.0000
12.000 1.0513 0.05515 0.04620 -0.0261 0.0248 1.0000
12.250 1.0517 0.05800 0.04915 -0.0256 0.0240 1.0000
12.500 1.0551 0.06058 0.05184 -0.0251 0.0231 1.0000
12.750 1.0617 0.06288 0.05428 -0.0248 0.0218 1.0000
13.000 1.0685 0.06518 0.05670 -0.0245 0.0207 1.0000
13.250 1.0758 0.06745 0.05907 -0.0242 0.0197 1.0000
13.500 1.0847 0.06958 0.06132 -0.0238 0.0191 1.0000
13.750 1.0955 0.07157 0.06339 -0.0234 0.0185 1.0000
14.000 1.1077 0.07348 0.06537 -0.0229 0.0180 1.0000
14.250 1.1234 0.07524 0.06718 -0.0223 0.0175 1.0000
14.500 1.1422 0.07713 0.06916 -0.0215 0.0171 1.0000
14.750 1.1518 0.07981 0.07208 -0.0214 0.0169 1.0000
15.000 1.1569 0.08295 0.07549 -0.0214 0.0167 1.0000
15.250 1.1577 0.08655 0.07937 -0.0217 0.0164 1.0000
15.500 1.1551 0.09058 0.08368 -0.0223 0.0161 1.0000
15.750 1.1502 0.09494 0.08831 -0.0233 0.0158 1.0000
16.000 1.1430 0.09970 0.09334 -0.0246 0.0156 1.0000
16.250 1.1339 0.10485 0.09876 -0.0264 0.0153 1.0000
16.500 1.1234 0.11039 0.10455 -0.0286 0.0152 1.0000
16.750 1.1113 0.11639 0.11079 -0.0313 0.0151 1.0000
17.000 1.0977 0.12293 0.11757 -0.0347 0.0150 1.0000
17.250 1.0829 0.13004 0.12490 -0.0387 0.0150 1.0000
17.500 1.0664 0.13789 0.13297 -0.0434 0.0151 1.0000
17.750 1.0490 0.14642 0.14169 -0.0488 0.0152 1.0000
18.000 1.0299 0.15606 0.15152 -0.0551 0.0154 1.0000
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