AH 82-150 A (ah82150a-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: AH 82-150 A (ah82150a-il) Reynolds number: 200,000 Max Cl/Cd: 72.78 at α=8° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-ah82150a-il-200000.txt Download as CSV file: xf-ah82150a-il-200000.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 = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.750 -0.1656 0.11753 0.11432 -0.0770 0.9679 0.0474
-12.500 -0.1578 0.11367 0.11044 -0.0800 0.9644 0.0492
-12.250 -0.3268 0.12423 0.12100 -0.0616 0.9907 0.0437
-12.000 -0.3063 0.12071 0.11745 -0.0633 0.9857 0.0450
-11.750 -0.2914 0.11669 0.11341 -0.0666 0.9802 0.0463
-11.500 -0.2784 0.11227 0.10896 -0.0707 0.9754 0.0487
-11.250 -0.2675 0.10716 0.10385 -0.0762 0.9718 0.0511
-11.000 -0.2688 0.09993 0.09664 -0.0878 0.9657 0.0540
-10.500 -0.2537 0.08666 0.08335 -0.0995 0.9577 0.0561
-10.250 -0.2256 0.08572 0.08236 -0.0987 0.9532 0.0593
-10.000 -0.2140 0.08051 0.07712 -0.1048 0.9473 0.0620
-9.750 -0.2123 0.07260 0.06919 -0.1156 0.9398 0.0647
-9.500 -0.2380 0.06436 0.06076 -0.1269 0.9267 0.0663
-9.250 -0.2680 0.06161 0.05778 -0.1271 0.9133 0.0669
-9.000 -0.2259 0.04418 0.04058 -0.1226 0.8934 0.0704
-8.750 -0.2303 0.04168 0.03803 -0.1212 0.8875 0.0715
-8.500 -0.2948 0.05157 0.04737 -0.1232 0.8900 0.0702
-8.250 -0.2838 0.04919 0.04495 -0.1226 0.8857 0.0721
-8.000 -0.2811 0.04711 0.04275 -0.1210 0.8799 0.0743
-7.750 -0.2810 0.04519 0.04050 -0.1188 0.8739 0.0790
-7.500 -0.2974 0.03386 0.02760 -0.1123 0.8682 0.0421
-7.250 -0.2891 0.03072 0.02406 -0.1103 0.8631 0.0433
-7.000 -0.2709 0.02855 0.02175 -0.1098 0.8595 0.0456
-6.750 -0.2483 0.02682 0.01976 -0.1092 0.8565 0.0469
-6.500 -0.2279 0.02548 0.01821 -0.1081 0.8524 0.0485
-6.250 -0.2063 0.02454 0.01707 -0.1072 0.8482 0.0514
-6.000 -0.1820 0.02392 0.01617 -0.1066 0.8450 0.0541
-5.750 -0.1556 0.02195 0.01407 -0.1064 0.8426 0.0568
-5.500 -0.1321 0.02123 0.01335 -0.1059 0.8394 0.0607
-5.250 -0.1109 0.02082 0.01287 -0.1050 0.8349 0.0650
-5.000 -0.0866 0.02032 0.01227 -0.1044 0.8317 0.0679
-4.750 -0.0641 0.01932 0.01135 -0.1037 0.8289 0.0734
-4.500 -0.0384 0.01889 0.01085 -0.1034 0.8266 0.0803
-4.250 -0.0236 0.01849 0.01052 -0.1016 0.8216 0.0862
-4.000 -0.0021 0.01820 0.01021 -0.1009 0.8180 0.0957
-3.750 0.0195 0.01756 0.00971 -0.1003 0.8150 0.1184
-3.500 0.0353 0.01586 0.00906 -0.0996 0.8125 0.3312
-3.250 0.0387 0.01558 0.01024 -0.0948 0.8073 0.6723
-3.000 0.0605 0.01636 0.01093 -0.0929 0.8036 0.7202
-2.750 0.0840 0.01702 0.01152 -0.0910 0.8009 0.7455
-2.500 0.1083 0.01753 0.01195 -0.0892 0.7986 0.7616
-2.250 0.1260 0.01816 0.01255 -0.0865 0.7950 0.7758
-2.000 0.1395 0.01879 0.01316 -0.0833 0.7899 0.7893
-1.750 0.1555 0.01936 0.01372 -0.0792 0.7868 0.8065
-1.500 0.1723 0.01985 0.01417 -0.0751 0.7845 0.8276
-1.250 0.1938 0.02010 0.01436 -0.0724 0.7827 0.8438
-1.000 0.1917 0.02070 0.01501 -0.0666 0.7750 0.8548
-0.750 0.2138 0.02070 0.01497 -0.0647 0.7721 0.8651
-0.500 0.2423 0.02056 0.01473 -0.0650 0.7700 0.8717
-0.250 0.2740 0.02033 0.01440 -0.0659 0.7683 0.8742
0.000 0.2733 0.02079 0.01491 -0.0616 0.7598 0.8780
0.250 0.3038 0.02059 0.01464 -0.0624 0.7572 0.8801
0.500 0.3377 0.02033 0.01430 -0.0637 0.7553 0.8821
0.750 0.3712 0.02012 0.01402 -0.0651 0.7533 0.8838
1.000 0.3761 0.02063 0.01456 -0.0625 0.7444 0.8871
1.250 0.4100 0.02032 0.01420 -0.0637 0.7422 0.8881
1.500 0.4450 0.02000 0.01383 -0.0650 0.7403 0.8893
1.750 0.4531 0.02042 0.01430 -0.0624 0.7323 0.8916
2.000 0.4853 0.02021 0.01406 -0.0635 0.7292 0.8927
2.250 0.5214 0.01988 0.01372 -0.0651 0.7270 0.8940
2.500 0.5586 0.01957 0.01337 -0.0669 0.7252 0.8951
2.750 0.5674 0.02009 0.01396 -0.0647 0.7165 0.8974
3.000 0.6033 0.01980 0.01366 -0.0664 0.7138 0.8984
3.250 0.6416 0.01945 0.01331 -0.0684 0.7117 0.8994
3.500 0.6579 0.01980 0.01372 -0.0672 0.7043 0.9017
3.750 0.6891 0.01956 0.01350 -0.0680 0.7005 0.9028
4.000 0.7262 0.01916 0.01313 -0.0697 0.6979 0.9037
4.250 0.7482 0.01924 0.01328 -0.0691 0.6920 0.9053
4.500 0.7757 0.01912 0.01321 -0.0693 0.6866 0.9069
4.750 0.8131 0.01872 0.01285 -0.0710 0.6837 0.9082
5.000 0.8360 0.01876 0.01297 -0.0706 0.6773 0.9106
5.250 0.8659 0.01858 0.01286 -0.0712 0.6717 0.9125
5.500 0.9061 0.01812 0.01244 -0.0734 0.6685 0.9136
5.750 0.9250 0.01826 0.01271 -0.0724 0.6599 0.9158
6.000 0.9608 0.01780 0.01230 -0.0737 0.6552 0.9171
6.250 0.9817 0.01774 0.01236 -0.0727 0.6471 0.9195
6.500 1.0158 0.01732 0.01201 -0.0737 0.6410 0.9214
6.750 1.0376 0.01712 0.01195 -0.0727 0.6310 0.9246
7.000 1.0648 0.01631 0.01117 -0.0720 0.6157 0.9276
7.250 1.0852 0.01553 0.01038 -0.0700 0.5929 0.9308
7.500 1.0999 0.01517 0.01002 -0.0674 0.5683 0.9347
8.000 1.1135 0.01530 0.01005 -0.0599 0.5036 0.9465
8.250 1.1140 0.01585 0.01038 -0.0556 0.4575 0.9559
8.500 1.1130 0.01695 0.01121 -0.0520 0.4028 0.9723
8.750 1.1053 0.01873 0.01264 -0.0486 0.3390 1.0000
9.000 1.0905 0.02128 0.01472 -0.0449 0.2605 1.0000
9.250 1.0678 0.02473 0.01748 -0.0411 0.1603 1.0000
9.500 1.0476 0.02836 0.02044 -0.0379 0.0695 1.0000
9.750 1.0425 0.03110 0.02293 -0.0359 0.0416 1.0000
10.000 1.0501 0.03292 0.02483 -0.0350 0.0360 1.0000
10.250 1.0516 0.03524 0.02719 -0.0338 0.0319 1.0000
10.500 1.0592 0.03709 0.02915 -0.0330 0.0302 1.0000
10.750 1.0649 0.03913 0.03131 -0.0322 0.0284 1.0000
11.000 1.0699 0.04127 0.03353 -0.0313 0.0274 1.0000
11.250 1.0752 0.04342 0.03574 -0.0305 0.0265 1.0000
11.500 1.0800 0.04564 0.03801 -0.0296 0.0256 1.0000
11.750 1.0865 0.04776 0.04016 -0.0287 0.0249 1.0000
12.000 1.0986 0.04954 0.04194 -0.0275 0.0241 1.0000
12.250 1.1207 0.05076 0.04320 -0.0266 0.0233 1.0000
12.500 1.1366 0.05223 0.04479 -0.0262 0.0224 1.0000
12.750 1.1573 0.05365 0.04633 -0.0256 0.0217 1.0000
13.000 1.1835 0.05515 0.04801 -0.0251 0.0215 1.0000
13.250 1.2083 0.05715 0.05022 -0.0247 0.0214 1.0000
13.500 1.2297 0.05985 0.05317 -0.0242 0.0217 1.0000
13.750 1.2441 0.06324 0.05685 -0.0236 0.0221 1.0000
14.000 1.2538 0.06745 0.06134 -0.0230 0.0227 1.0000
14.250 1.2799 0.07128 0.06534 -0.0230 0.0241 1.0000
14.500 1.2549 0.08290 0.07781 -0.0211 0.0315 1.0000
14.750 1.2323 0.08574 0.08088 -0.0204 0.0311 1.0000
16.000 0.9522 0.10598 0.10276 -0.0226 0.0276 1.0000
16.250 0.9227 0.11318 0.11018 -0.0269 0.0280 1.0000
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