AH 82-150 A (ah82150a-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: AH 82-150 A (ah82150a-il) Reynolds number: 1,000,000 Max Cl/Cd: 137.58 at α=5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-ah82150a-il-1000000.txt Download as CSV file: xf-ah82150a-il-1000000.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 = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-13.750 -0.6101 0.05210 0.05007 -0.1073 0.9391 0.0082
-13.500 -0.6140 0.04156 0.03906 -0.1232 0.9177 0.0085
-13.250 -0.6262 0.03635 0.03344 -0.1272 0.8874 0.0083
-13.000 -0.6337 0.03368 0.03051 -0.1268 0.8686 0.0086
-12.750 -0.6446 0.03102 0.02759 -0.1254 0.8548 0.0086
-12.500 -0.6493 0.02897 0.02533 -0.1236 0.8443 0.0087
-12.250 -0.6505 0.02724 0.02340 -0.1218 0.8359 0.0088
-12.000 -0.6446 0.02614 0.02215 -0.1201 0.8287 0.0090
-11.750 -0.6476 0.02425 0.02004 -0.1175 0.8219 0.0090
-11.500 -0.6310 0.02410 0.01982 -0.1164 0.8163 0.0093
-11.250 -0.6204 0.02353 0.01914 -0.1146 0.8111 0.0093
-11.000 -0.6352 0.02064 0.01589 -0.1097 0.8056 0.0097
-10.750 -0.6249 0.01945 0.01454 -0.1078 0.8012 0.0101
-10.500 -0.6091 0.01871 0.01368 -0.1066 0.7971 0.0103
-10.250 -0.5898 0.01825 0.01318 -0.1057 0.7935 0.0107
-10.000 -0.5702 0.01771 0.01258 -0.1049 0.7898 0.0110
-9.750 -0.5506 0.01709 0.01185 -0.1040 0.7863 0.0114
-9.500 -0.5303 0.01650 0.01115 -0.1033 0.7830 0.0118
-9.250 -0.5090 0.01593 0.01049 -0.1026 0.7801 0.0122
-9.000 -0.4868 0.01545 0.00993 -0.1021 0.7771 0.0126
-8.750 -0.4635 0.01508 0.00949 -0.1016 0.7740 0.0129
-8.500 -0.4462 0.01399 0.00826 -0.1004 0.7709 0.0139
-8.250 -0.4228 0.01362 0.00785 -0.1000 0.7678 0.0148
-8.000 -0.3980 0.01336 0.00759 -0.0998 0.7654 0.0156
-7.750 -0.3728 0.01313 0.00731 -0.0997 0.7627 0.0166
-7.500 -0.3467 0.01298 0.00713 -0.0996 0.7600 0.0175
-7.250 -0.3254 0.01229 0.00635 -0.0989 0.7573 0.0188
-7.000 -0.3006 0.01199 0.00603 -0.0987 0.7545 0.0202
-6.750 -0.2747 0.01178 0.00581 -0.0986 0.7522 0.0216
-6.500 -0.2486 0.01158 0.00559 -0.0986 0.7497 0.0229
-6.250 -0.2219 0.01144 0.00541 -0.0986 0.7472 0.0238
-6.000 -0.1990 0.01085 0.00476 -0.0981 0.7446 0.0262
-5.750 -0.1727 0.01066 0.00457 -0.0982 0.7422 0.0282
-5.500 -0.1459 0.01051 0.00438 -0.0982 0.7397 0.0301
-5.250 -0.1188 0.01037 0.00423 -0.0983 0.7375 0.0316
-5.000 -0.0930 0.01006 0.00388 -0.0983 0.7351 0.0335
-4.750 -0.0670 0.00974 0.00354 -0.0982 0.7327 0.0368
-4.500 -0.0400 0.00955 0.00334 -0.0983 0.7304 0.0396
-4.250 -0.0125 0.00943 0.00318 -0.0985 0.7281 0.0419
-4.000 0.0145 0.00922 0.00293 -0.0986 0.7257 0.0466
-3.750 0.0419 0.00904 0.00277 -0.0988 0.7235 0.0529
-3.500 0.0691 0.00882 0.00260 -0.0990 0.7213 0.0655
-3.250 0.0959 0.00851 0.00243 -0.0992 0.7189 0.1024
-3.000 0.1221 0.00806 0.00226 -0.0994 0.7165 0.1819
-2.750 0.1484 0.00755 0.00209 -0.0998 0.7142 0.2855
-2.500 0.1739 0.00664 0.00181 -0.1005 0.7118 0.4851
-2.250 0.2009 0.00611 0.00182 -0.1009 0.7095 0.6601
-2.000 0.2300 0.00613 0.00184 -0.1012 0.7072 0.6829
-1.750 0.2590 0.00617 0.00188 -0.1016 0.7047 0.6953
-1.500 0.2880 0.00623 0.00192 -0.1019 0.7021 0.7054
-1.250 0.3172 0.00630 0.00193 -0.1023 0.6996 0.7124
-1.000 0.3458 0.00648 0.00210 -0.1024 0.6967 0.7261
-0.750 0.3736 0.00663 0.00229 -0.1023 0.6939 0.7372
-0.500 0.4024 0.00671 0.00235 -0.1026 0.6905 0.7431
-0.250 0.4304 0.00674 0.00240 -0.1026 0.6871 0.7474
0.000 0.4587 0.00684 0.00248 -0.1028 0.6839 0.7521
0.250 0.4876 0.00691 0.00251 -0.1032 0.6808 0.7550
0.500 0.5166 0.00691 0.00251 -0.1036 0.6779 0.7561
0.750 0.5456 0.00691 0.00250 -0.1041 0.6748 0.7570
1.000 0.5744 0.00689 0.00246 -0.1045 0.6716 0.7580
1.250 0.6031 0.00690 0.00244 -0.1049 0.6684 0.7589
1.500 0.6317 0.00690 0.00245 -0.1053 0.6652 0.7597
1.750 0.6602 0.00689 0.00246 -0.1056 0.6616 0.7606
2.000 0.6887 0.00689 0.00247 -0.1060 0.6580 0.7615
2.250 0.7171 0.00693 0.00250 -0.1063 0.6543 0.7626
2.500 0.7455 0.00695 0.00253 -0.1066 0.6507 0.7635
2.750 0.7740 0.00696 0.00256 -0.1070 0.6465 0.7644
3.000 0.8022 0.00698 0.00260 -0.1073 0.6424 0.7653
3.250 0.8303 0.00704 0.00264 -0.1076 0.6382 0.7663
3.500 0.8585 0.00704 0.00269 -0.1079 0.6335 0.7673
3.750 0.8864 0.00708 0.00273 -0.1081 0.6282 0.7682
4.000 0.9141 0.00714 0.00280 -0.1083 0.6228 0.7693
4.250 0.9419 0.00717 0.00287 -0.1086 0.6163 0.7704
4.500 0.9688 0.00724 0.00293 -0.1086 0.6080 0.7713
4.750 0.9946 0.00732 0.00298 -0.1084 0.5942 0.7721
5.000 1.0195 0.00741 0.00306 -0.1081 0.5755 0.7733
5.250 1.0421 0.00761 0.00318 -0.1073 0.5498 0.7744
5.500 1.0619 0.00795 0.00339 -0.1060 0.5140 0.7755
5.750 1.0766 0.00852 0.00373 -0.1038 0.4629 0.7767
6.000 1.0905 0.00914 0.00413 -0.1015 0.4157 0.7780
6.250 1.1047 0.00972 0.00453 -0.0993 0.3758 0.7793
6.500 1.1139 0.01045 0.00502 -0.0962 0.3261 0.7809
6.750 1.1126 0.01138 0.00562 -0.0912 0.2657 0.7828
7.000 1.1018 0.01260 0.00645 -0.0846 0.1964 0.7847
7.250 1.0883 0.01410 0.00756 -0.0780 0.1260 0.7863
7.500 1.0767 0.01569 0.00882 -0.0723 0.0628 0.7885
7.750 1.0714 0.01721 0.01011 -0.0679 0.0194 0.7903
8.000 1.0829 0.01800 0.01092 -0.0660 0.0144 0.7920
8.250 1.0936 0.01887 0.01185 -0.0640 0.0122 0.7937
8.500 1.1084 0.01955 0.01257 -0.0626 0.0117 0.7954
8.750 1.1220 0.02031 0.01338 -0.0612 0.0111 0.7972
9.000 1.1356 0.02109 0.01420 -0.0599 0.0104 0.7989
9.250 1.1478 0.02200 0.01514 -0.0584 0.0098 0.8005
9.500 1.1573 0.02307 0.01627 -0.0567 0.0092 0.8027
9.750 1.1613 0.02455 0.01787 -0.0544 0.0087 0.8049
10.000 1.1716 0.02565 0.01904 -0.0529 0.0084 0.8072
10.250 1.1835 0.02667 0.02012 -0.0516 0.0081 0.8094
10.500 1.1937 0.02783 0.02134 -0.0503 0.0079 0.8117
10.750 1.2022 0.02916 0.02273 -0.0489 0.0076 0.8139
11.000 1.2105 0.03054 0.02418 -0.0475 0.0075 0.8162
11.250 1.2197 0.03184 0.02555 -0.0463 0.0072 0.8188
11.500 1.2268 0.03336 0.02715 -0.0450 0.0070 0.8215
11.750 1.2336 0.03496 0.02884 -0.0438 0.0069 0.8244
12.000 1.2407 0.03660 0.03053 -0.0427 0.0066 0.8274
12.250 1.2458 0.03845 0.03244 -0.0415 0.0064 0.8303
12.500 1.2467 0.04072 0.03480 -0.0402 0.0062 0.8337
12.750 1.2372 0.04410 0.03831 -0.0382 0.0059 0.8369
13.000 1.2461 0.04580 0.04009 -0.0376 0.0058 0.8409
13.250 1.2553 0.04751 0.04189 -0.0370 0.0057 0.8452
13.500 1.2640 0.04927 0.04375 -0.0365 0.0056 0.8506
13.750 1.2714 0.05122 0.04580 -0.0360 0.0054 0.8566
14.000 1.2769 0.05340 0.04809 -0.0353 0.0054 0.8633
14.250 1.2835 0.05551 0.05032 -0.0348 0.0053 0.8723
14.500 1.2892 0.05766 0.05263 -0.0343 0.0052 0.8862
14.750 1.2926 0.05968 0.05492 -0.0332 0.0051 0.9603
15.000 1.2981 0.06207 0.05740 -0.0331 0.0050 1.0000
15.250 1.3036 0.06457 0.05999 -0.0331 0.0049 1.0000
15.500 1.3076 0.06736 0.06288 -0.0330 0.0049 1.0000
15.750 1.3112 0.07021 0.06585 -0.0330 0.0048 1.0000
16.000 1.3139 0.07321 0.06894 -0.0334 0.0047 1.0000
16.250 1.3153 0.07648 0.07232 -0.0337 0.0046 1.0000
16.500 1.3151 0.08005 0.07603 -0.0342 0.0046 1.0000
16.750 1.3147 0.08367 0.07975 -0.0350 0.0045 1.0000
17.000 1.3126 0.08767 0.08388 -0.0359 0.0045 1.0000
17.250 1.3096 0.09184 0.08818 -0.0370 0.0045 1.0000
17.500 1.3069 0.09604 0.09249 -0.0385 0.0044 1.0000
17.750 1.2995 0.10116 0.09777 -0.0401 0.0044 1.0000
18.000 1.2905 0.10668 0.10346 -0.0421 0.0044 1.0000
18.250 1.2859 0.11149 0.10836 -0.0444 0.0043 1.0000
18.500 1.2779 0.11703 0.11403 -0.0469 0.0043 1.0000
18.750 1.2667 0.12328 0.12044 -0.0499 0.0043 1.0000
19.000 1.2573 0.12934 0.12663 -0.0531 0.0042 1.0000
19.250 1.2467 0.13577 0.13319 -0.0567 0.0042 1.0000
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Polar data table (+)
Polar graphs
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