AH 82-150 A (ah82150a-il) Xfoil prediction polar at RE=500,000 Ncrit=9
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Airfoil: AH 82-150 A (ah82150a-il) Reynolds number: 500,000 Max Cl/Cd: 108.69 at α=6° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-ah82150a-il-500000.txt Download as CSV file: xf-ah82150a-il-500000.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 = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.500 -0.2227 0.08645 0.08382 -0.1069 0.8955 0.0250
-11.250 -0.2240 0.08101 0.07831 -0.1106 0.8847 0.0250
-11.000 -0.3195 0.05348 0.05059 -0.1265 0.8715 0.0170
-10.750 -0.3500 0.04807 0.04498 -0.1277 0.8607 0.0168
-10.500 -0.3750 0.04407 0.04078 -0.1269 0.8520 0.0166
-10.250 -0.4069 0.03975 0.03617 -0.1240 0.8434 0.0166
-10.000 -0.4337 0.03654 0.03271 -0.1195 0.8362 0.0166
-9.750 -0.4513 0.03295 0.02875 -0.1155 0.8301 0.0165
-9.500 -0.4579 0.02956 0.02494 -0.1123 0.8253 0.0166
-9.250 -0.4539 0.02700 0.02204 -0.1100 0.8206 0.0170
-9.000 -0.4420 0.02524 0.01996 -0.1083 0.8166 0.0174
-8.750 -0.4253 0.02412 0.01858 -0.1072 0.8132 0.0177
-8.500 -0.4135 0.02108 0.01524 -0.1058 0.8099 0.0188
-8.250 -0.3919 0.02076 0.01490 -0.1053 0.8063 0.0198
-8.000 -0.3699 0.02017 0.01421 -0.1048 0.8029 0.0208
-7.750 -0.3472 0.01935 0.01323 -0.1043 0.7998 0.0220
-7.500 -0.3233 0.01866 0.01237 -0.1039 0.7971 0.0232
-7.250 -0.2993 0.01831 0.01191 -0.1035 0.7942 0.0239
-7.000 -0.2786 0.01641 0.00992 -0.1028 0.7911 0.0260
-6.750 -0.2544 0.01600 0.00948 -0.1025 0.7881 0.0277
-6.500 -0.2291 0.01575 0.00915 -0.1023 0.7853 0.0299
-6.250 -0.2034 0.01548 0.00878 -0.1022 0.7829 0.0315
-6.000 -0.1818 0.01448 0.00773 -0.1014 0.7801 0.0337
-5.750 -0.1584 0.01401 0.00726 -0.1010 0.7771 0.0364
-5.500 -0.1334 0.01369 0.00691 -0.1008 0.7743 0.0390
-5.250 -0.1081 0.01337 0.00651 -0.1006 0.7717 0.0412
-5.000 -0.0833 0.01299 0.00605 -0.1003 0.7694 0.0433
-4.750 -0.0602 0.01246 0.00552 -0.0999 0.7669 0.0476
-4.500 -0.0352 0.01217 0.00523 -0.0996 0.7640 0.0513
-4.250 -0.0091 0.01197 0.00497 -0.0996 0.7612 0.0544
-4.000 0.0158 0.01155 0.00457 -0.0994 0.7587 0.0623
-3.750 0.0422 0.01127 0.00427 -0.0994 0.7564 0.0730
-3.500 0.0679 0.01087 0.00400 -0.0995 0.7541 0.1104
-3.250 0.0901 0.01004 0.00375 -0.0994 0.7515 0.2532
-3.000 0.1110 0.00869 0.00336 -0.0996 0.7487 0.5071
-2.750 0.1358 0.00844 0.00365 -0.0991 0.7460 0.6751
-2.500 0.1647 0.00858 0.00372 -0.0993 0.7435 0.6995
-2.250 0.1934 0.00876 0.00384 -0.0994 0.7413 0.7150
-2.000 0.2225 0.00900 0.00399 -0.0996 0.7391 0.7276
-1.750 0.2492 0.00913 0.00417 -0.0993 0.7364 0.7348
-1.500 0.2761 0.00936 0.00439 -0.0990 0.7335 0.7462
-1.250 0.3011 0.00978 0.00486 -0.0978 0.7308 0.7620
-1.000 0.3288 0.01003 0.00506 -0.0976 0.7283 0.7720
-0.750 0.3549 0.01019 0.00523 -0.0969 0.7259 0.7775
-0.500 0.3820 0.01037 0.00539 -0.0967 0.7232 0.7843
-0.250 0.4092 0.01036 0.00538 -0.0967 0.7198 0.7879
0.000 0.4371 0.01032 0.00532 -0.0969 0.7164 0.7893
0.250 0.4659 0.01027 0.00523 -0.0973 0.7134 0.7906
0.500 0.4955 0.01027 0.00516 -0.0979 0.7105 0.7918
0.750 0.5227 0.01023 0.00515 -0.0980 0.7067 0.7933
1.000 0.5510 0.01019 0.00510 -0.0984 0.7030 0.7946
1.250 0.5803 0.01014 0.00502 -0.0989 0.6997 0.7958
1.500 0.6101 0.01013 0.00497 -0.0996 0.6969 0.7971
1.750 0.6384 0.01013 0.00498 -0.1000 0.6934 0.7986
2.000 0.6667 0.01010 0.00496 -0.1005 0.6895 0.7997
2.250 0.6961 0.01008 0.00493 -0.1011 0.6859 0.8007
2.500 0.7253 0.01004 0.00487 -0.1016 0.6827 0.8016
2.750 0.7524 0.01003 0.00490 -0.1017 0.6787 0.8026
3.000 0.7797 0.01001 0.00491 -0.1019 0.6743 0.8038
3.250 0.8081 0.00999 0.00491 -0.1022 0.6704 0.8048
3.500 0.8369 0.01000 0.00492 -0.1026 0.6666 0.8058
3.750 0.8634 0.01000 0.00499 -0.1027 0.6616 0.8069
4.000 0.8913 0.00998 0.00501 -0.1029 0.6569 0.8080
4.250 0.9200 0.01000 0.00502 -0.1033 0.6526 0.8091
4.500 0.9461 0.01000 0.00510 -0.1033 0.6465 0.8104
4.750 0.9738 0.01000 0.00512 -0.1035 0.6409 0.8120
5.000 1.0006 0.01002 0.00520 -0.1035 0.6344 0.8134
5.250 1.0271 0.01000 0.00518 -0.1035 0.6253 0.8146
5.500 1.0510 0.00996 0.00517 -0.1029 0.6113 0.8157
5.750 1.0728 0.00995 0.00518 -0.1018 0.5915 0.8169
6.000 1.0923 0.01005 0.00524 -0.1003 0.5643 0.8182
6.250 1.1090 0.01032 0.00539 -0.0984 0.5299 0.8197
6.500 1.1222 0.01075 0.00567 -0.0958 0.4904 0.8213
6.750 1.1307 0.01135 0.00607 -0.0925 0.4470 0.8232
7.000 1.1327 0.01209 0.00659 -0.0881 0.4009 0.8257
7.250 1.1297 0.01293 0.00719 -0.0828 0.3560 0.8282
7.500 1.1221 0.01410 0.00806 -0.0772 0.3005 0.8304
7.750 1.1079 0.01567 0.00927 -0.0711 0.2327 0.8329
8.000 1.0882 0.01782 0.01094 -0.0648 0.1509 0.8358
8.250 1.0667 0.02043 0.01304 -0.0590 0.0647 0.8388
8.500 1.0605 0.02243 0.01477 -0.0554 0.0235 0.8415
8.750 1.0709 0.02350 0.01589 -0.0538 0.0200 0.8438
9.000 1.0793 0.02467 0.01714 -0.0519 0.0177 0.8462
9.250 1.0883 0.02583 0.01841 -0.0502 0.0167 0.8489
9.500 1.0987 0.02695 0.01961 -0.0487 0.0160 0.8519
9.750 1.1077 0.02821 0.02096 -0.0472 0.0153 0.8550
10.000 1.1165 0.02953 0.02235 -0.0459 0.0145 0.8580
10.250 1.1232 0.03098 0.02389 -0.0443 0.0136 0.8610
10.500 1.1272 0.03267 0.02566 -0.0426 0.0130 0.8645
10.750 1.1226 0.03516 0.02827 -0.0404 0.0124 0.8684
11.000 1.1253 0.03720 0.03040 -0.0389 0.0121 0.8723
11.250 1.1343 0.03864 0.03195 -0.0378 0.0119 0.8766
11.500 1.1412 0.04033 0.03374 -0.0367 0.0117 0.8817
11.750 1.1482 0.04209 0.03560 -0.0356 0.0115 0.8876
12.000 1.1550 0.04380 0.03743 -0.0344 0.0111 0.8952
12.250 1.1620 0.04548 0.03922 -0.0332 0.0109 0.9060
12.500 1.1692 0.04709 0.04100 -0.0319 0.0107 0.9306
12.750 1.1799 0.04880 0.04283 -0.0315 0.0104 1.0000
13.000 1.1920 0.05052 0.04462 -0.0309 0.0103 1.0000
13.250 1.2048 0.05222 0.04639 -0.0304 0.0100 1.0000
13.500 1.2183 0.05391 0.04816 -0.0300 0.0099 1.0000
13.750 1.2293 0.05578 0.05009 -0.0297 0.0096 1.0000
14.000 1.2414 0.05767 0.05207 -0.0293 0.0094 1.0000
14.250 1.2529 0.05969 0.05414 -0.0290 0.0091 1.0000
14.500 1.2690 0.06186 0.05640 -0.0286 0.0088 1.0000
14.750 1.2777 0.06446 0.05918 -0.0282 0.0089 1.0000
15.000 1.2833 0.06745 0.06234 -0.0279 0.0089 1.0000
15.250 1.2852 0.07081 0.06589 -0.0277 0.0089 1.0000
15.500 1.2824 0.07432 0.06959 -0.0277 0.0090 1.0000
15.750 1.1143 0.08742 0.08361 -0.0303 0.0094 0.8967
16.000 1.0684 0.09674 0.09352 -0.0331 0.0105 0.8907
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