AH 82-150 F (ah82150f-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: AH 82-150 F (ah82150f-il) Reynolds number: 500,000 Max Cl/Cd: 95.65 at α=6.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-ah82150f-il-500000.txt Download as CSV file: xf-ah82150f-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: AH 82-150 F
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
------ -------- --------- --------- -------- -------- --------
-11.250 -0.1312 0.08845 0.08530 -0.1253 0.8351 0.0229
-11.000 -0.1327 0.08394 0.08080 -0.1274 0.8343 0.0230
-10.750 -0.1358 0.07906 0.07594 -0.1299 0.8334 0.0230
-9.500 -0.2829 0.04501 0.04161 -0.1347 0.8268 0.0153
-9.250 -0.3051 0.04217 0.03860 -0.1295 0.8250 0.0155
-9.000 -0.3190 0.03908 0.03529 -0.1253 0.8237 0.0155
-8.750 -0.3312 0.03563 0.03155 -0.1210 0.8225 0.0155
-8.500 -0.3393 0.03208 0.02765 -0.1168 0.8214 0.0153
-8.250 -0.3416 0.02860 0.02375 -0.1129 0.8204 0.0153
-8.000 -0.3340 0.02605 0.02082 -0.1101 0.8195 0.0155
-7.750 -0.3197 0.02427 0.01873 -0.1083 0.8188 0.0158
-7.500 -0.3020 0.02300 0.01720 -0.1069 0.8180 0.0162
-7.250 -0.2858 0.02006 0.01392 -0.1055 0.8172 0.0171
-7.000 -0.2644 0.01918 0.01296 -0.1048 0.8162 0.0179
-6.750 -0.2420 0.01863 0.01235 -0.1043 0.8154 0.0188
-6.500 -0.2190 0.01849 0.01216 -0.1038 0.8145 0.0205
-6.250 -0.1956 0.01810 0.01169 -0.1033 0.8136 0.0222
-6.000 -0.1737 0.01719 0.01068 -0.1025 0.8127 0.0239
-5.750 -0.1528 0.01656 0.01004 -0.1017 0.8117 0.0268
-5.500 -0.1294 0.01634 0.00979 -0.1012 0.8105 0.0297
-5.250 -0.1051 0.01623 0.00962 -0.1008 0.8096 0.0321
-5.000 -0.0854 0.01561 0.00897 -0.0997 0.8087 0.0365
-4.750 -0.0614 0.01549 0.00884 -0.0993 0.8079 0.0406
-4.500 -0.0363 0.01544 0.00874 -0.0991 0.8070 0.0438
-4.250 -0.0158 0.01492 0.00820 -0.0980 0.8060 0.0491
-4.000 0.0082 0.01478 0.00803 -0.0976 0.8052 0.0540
-3.750 0.0317 0.01463 0.00783 -0.0971 0.8044 0.0599
-3.500 0.0535 0.01456 0.00778 -0.0963 0.8032 0.0683
-3.250 0.0712 0.01452 0.00782 -0.0949 0.8010 0.0821
-3.000 0.0875 0.01422 0.00783 -0.0933 0.7987 0.1480
-2.750 0.0998 0.01346 0.00778 -0.0912 0.7966 0.3328
-2.500 0.1129 0.01262 0.00763 -0.0890 0.7948 0.5223
-2.250 0.1223 0.01200 0.00801 -0.0849 0.7934 0.7704
-2.000 0.1495 0.01225 0.00821 -0.0847 0.7924 0.8191
-1.750 0.1760 0.01259 0.00851 -0.0840 0.7914 0.8365
-1.500 0.2032 0.01285 0.00868 -0.0837 0.7905 0.8478
-1.250 0.2150 0.01347 0.00935 -0.0806 0.7864 0.8548
-1.000 0.2320 0.01390 0.00979 -0.0782 0.7833 0.8653
-0.750 0.2501 0.01433 0.01022 -0.0752 0.7813 0.8795
-0.500 0.2717 0.01458 0.01045 -0.0728 0.7800 0.8924
-0.250 0.3015 0.01456 0.01038 -0.0728 0.7789 0.8981
0.000 0.3320 0.01441 0.01017 -0.0735 0.7777 0.9028
0.250 0.3634 0.01432 0.01003 -0.0737 0.7767 0.9063
0.500 0.3641 0.01478 0.01054 -0.0684 0.7708 0.9167
0.750 0.3990 0.01475 0.01050 -0.0693 0.7689 0.9221
1.000 0.4316 0.01460 0.01032 -0.0703 0.7673 0.9257
1.250 0.4568 0.01439 0.01008 -0.0699 0.7656 0.9289
1.500 0.4855 0.01414 0.00980 -0.0703 0.7643 0.9305
1.750 0.5195 0.01388 0.00951 -0.0718 0.7632 0.9310
2.000 0.5532 0.01369 0.00929 -0.0732 0.7621 0.9313
2.250 0.5564 0.01380 0.00948 -0.0688 0.7558 0.9336
2.500 0.5851 0.01357 0.00925 -0.0693 0.7535 0.9342
2.750 0.6167 0.01332 0.00899 -0.0703 0.7518 0.9346
3.000 0.6508 0.01305 0.00872 -0.0718 0.7504 0.9351
3.250 0.6859 0.01279 0.00845 -0.0735 0.7491 0.9352
3.500 0.6968 0.01278 0.00850 -0.0706 0.7439 0.9368
3.750 0.7216 0.01257 0.00833 -0.0703 0.7404 0.9375
4.000 0.7540 0.01230 0.00808 -0.0715 0.7382 0.9380
4.250 0.7891 0.01199 0.00777 -0.0732 0.7363 0.9383
4.500 0.8139 0.01180 0.00764 -0.0729 0.7326 0.9389
4.750 0.8325 0.01165 0.00755 -0.0714 0.7271 0.9399
5.000 0.8641 0.01135 0.00730 -0.0724 0.7239 0.9402
5.250 0.8881 0.01102 0.00701 -0.0719 0.7175 0.9409
5.500 0.9146 0.01048 0.00649 -0.0716 0.7085 0.9415
5.750 0.9254 0.01023 0.00630 -0.0684 0.6957 0.9432
6.000 0.9354 0.01001 0.00613 -0.0650 0.6816 0.9445
6.250 0.9412 0.00984 0.00593 -0.0607 0.6553 0.9462
6.500 0.9492 0.00993 0.00582 -0.0571 0.6157 0.9478
6.750 0.9466 0.01050 0.00617 -0.0518 0.5737 0.9502
7.000 0.9376 0.01141 0.00686 -0.0458 0.5305 0.9536
7.250 0.9278 0.01259 0.00780 -0.0403 0.4856 0.9564
7.500 0.9166 0.01398 0.00893 -0.0348 0.4330 0.9595
7.750 0.9113 0.01531 0.01001 -0.0306 0.3840 0.9626
8.000 0.9013 0.01702 0.01133 -0.0259 0.3112 0.9663
8.250 0.8842 0.01932 0.01295 -0.0207 0.1943 0.9703
8.500 0.8691 0.02209 0.01493 -0.0166 0.0558 0.9742
8.750 0.8781 0.02362 0.01629 -0.0153 0.0200 0.9773
9.000 0.8974 0.02452 0.01728 -0.0153 0.0169 0.9799
9.250 0.9158 0.02548 0.01831 -0.0152 0.0152 0.9826
9.500 0.9305 0.02666 0.01958 -0.0148 0.0140 0.9895
9.750 0.9368 0.02822 0.02124 -0.0130 0.0130 1.0000
10.000 0.9441 0.02968 0.02280 -0.0114 0.0126 1.0000
10.250 0.9538 0.03104 0.02423 -0.0102 0.0123 1.0000
10.500 0.9649 0.03233 0.02559 -0.0091 0.0119 1.0000
10.750 0.9772 0.03354 0.02687 -0.0083 0.0110 1.0000
11.000 0.9868 0.03498 0.02837 -0.0072 0.0104 1.0000
11.250 0.9953 0.03656 0.03002 -0.0060 0.0102 1.0000
11.500 1.0047 0.03809 0.03161 -0.0050 0.0097 1.0000
11.750 1.0150 0.03959 0.03315 -0.0041 0.0094 1.0000
12.000 1.0258 0.04111 0.03473 -0.0030 0.0093 1.0000
12.250 1.0391 0.04255 0.03621 -0.0021 0.0090 1.0000
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Polar data table (+)
Polar graphs
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