AH 82-150 F (ah82150f-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: AH 82-150 F (ah82150f-il) Reynolds number: 200,000 Max Cl/Cd: 53.06 at α=7.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-ah82150f-il-200000-n5.txt Download as CSV file: xf-ah82150f-il-200000-n5.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 = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.750 -0.1670 0.09438 0.08991 -0.1165 0.8433 0.0150
-11.500 -0.1703 0.08976 0.08533 -0.1184 0.8421 0.0151
-11.250 -0.1726 0.08559 0.08119 -0.1203 0.8410 0.0149
-11.000 -0.1803 0.08034 0.07598 -0.1226 0.8397 0.0148
-10.750 -0.1903 0.07469 0.07038 -0.1253 0.8382 0.0148
-10.500 -0.2040 0.06817 0.06390 -0.1293 0.8365 0.0145
-10.250 -0.2343 0.05896 0.05465 -0.1354 0.8345 0.0144
-10.000 -0.2580 0.05409 0.04965 -0.1358 0.8330 0.0141
-9.750 -0.2833 0.04986 0.04526 -0.1340 0.8314 0.0140
-9.500 -0.3067 0.04641 0.04166 -0.1304 0.8295 0.0140
-9.250 -0.3295 0.04325 0.03829 -0.1256 0.8275 0.0141
-9.000 -0.3447 0.03976 0.03448 -0.1213 0.8257 0.0141
-8.750 -0.3540 0.03631 0.03062 -0.1173 0.8239 0.0144
-8.500 -0.3552 0.03332 0.02718 -0.1138 0.8222 0.0148
-8.250 -0.3492 0.03078 0.02418 -0.1111 0.8209 0.0154
-8.000 -0.3374 0.02894 0.02194 -0.1091 0.8199 0.0164
-7.750 -0.3214 0.02784 0.02070 -0.1079 0.8191 0.0172
-7.500 -0.3029 0.02701 0.01972 -0.1069 0.8183 0.0182
-7.250 -0.2835 0.02579 0.01827 -0.1059 0.8175 0.0190
-7.000 -0.2644 0.02472 0.01699 -0.1048 0.8162 0.0201
-6.750 -0.2440 0.02372 0.01580 -0.1038 0.8149 0.0214
-6.500 -0.2229 0.02293 0.01480 -0.1029 0.8133 0.0227
-6.250 -0.2032 0.02220 0.01403 -0.1019 0.8118 0.0250
-6.000 -0.1824 0.02195 0.01374 -0.1012 0.8106 0.0277
-5.750 -0.1608 0.02149 0.01318 -0.1003 0.8094 0.0305
-5.500 -0.1393 0.02103 0.01261 -0.0995 0.8084 0.0329
-5.250 -0.1189 0.02056 0.01215 -0.0986 0.8073 0.0369
-5.000 -0.0968 0.02019 0.01169 -0.0978 0.8062 0.0404
-4.750 -0.0740 0.01989 0.01128 -0.0972 0.8052 0.0438
-4.500 -0.0534 0.01944 0.01085 -0.0962 0.8043 0.0490
-4.250 -0.0339 0.01929 0.01065 -0.0951 0.8031 0.0535
-4.000 -0.0227 0.01948 0.01080 -0.0925 0.7999 0.0568
-3.750 -0.0078 0.01939 0.01075 -0.0906 0.7976 0.0639
-3.500 0.0112 0.01930 0.01062 -0.0893 0.7957 0.0728
-3.250 0.0319 0.01909 0.01043 -0.0883 0.7941 0.0868
-3.000 0.0526 0.01877 0.01026 -0.0874 0.7928 0.1217
-2.750 0.0702 0.01811 0.01007 -0.0861 0.7915 0.2385
-2.500 0.0865 0.01732 0.00986 -0.0845 0.7904 0.3931
-2.250 0.0792 0.01761 0.01055 -0.0788 0.7841 0.4820
-2.000 0.0841 0.01717 0.01098 -0.0740 0.7813 0.6731
-1.750 0.1021 0.01789 0.01198 -0.0703 0.7796 0.8010
-1.500 0.1237 0.01807 0.01205 -0.0690 0.7782 0.8330
-1.250 0.1433 0.01855 0.01248 -0.0662 0.7770 0.8616
-1.000 0.1269 0.01951 0.01347 -0.0580 0.7687 0.8754
-0.750 0.1441 0.01989 0.01382 -0.0548 0.7665 0.8928
-0.500 0.1683 0.01996 0.01382 -0.0536 0.7651 0.9042
-0.250 0.1962 0.02005 0.01384 -0.0529 0.7640 0.9165
0.000 0.1866 0.02075 0.01457 -0.0460 0.7558 0.9289
0.250 0.2762 0.02002 0.01365 -0.0575 0.7627 0.9260
0.750 0.2780 0.02036 0.01397 -0.0482 0.7507 0.9345
1.000 0.2843 0.02052 0.01411 -0.0447 0.7452 0.9378
1.250 0.3360 0.01996 0.01346 -0.0491 0.7472 0.9366
1.750 0.3257 0.02059 0.01409 -0.0381 0.7311 0.9448
2.000 0.3740 0.01983 0.01328 -0.0416 0.7338 0.9439
2.500 0.4069 0.02006 0.01350 -0.0386 0.7226 0.9469
2.750 0.4357 0.01985 0.01328 -0.0390 0.7204 0.9477
3.250 0.4516 0.02064 0.01412 -0.0336 0.7030 0.9530
3.500 0.5039 0.01960 0.01308 -0.0374 0.7078 0.9516
3.750 0.5051 0.02023 0.01373 -0.0338 0.6963 0.9548
4.000 0.5368 0.01984 0.01337 -0.0345 0.6948 0.9553
4.500 0.5635 0.02065 0.01428 -0.0313 0.6758 0.9597
4.750 0.5898 0.02054 0.01421 -0.0315 0.6707 0.9608
5.000 0.6211 0.02018 0.01390 -0.0322 0.6681 0.9614
5.250 0.6370 0.02059 0.01438 -0.0312 0.6572 0.9634
5.750 0.6882 0.02048 0.01439 -0.0313 0.6435 0.9661
6.000 0.7152 0.02034 0.01434 -0.0315 0.6358 0.9674
6.250 0.7461 0.01998 0.01405 -0.0321 0.6293 0.9685
6.500 0.7752 0.01974 0.01388 -0.0326 0.6210 0.9697
6.750 0.8107 0.01915 0.01336 -0.0338 0.6142 0.9704
7.000 0.8436 0.01879 0.01309 -0.0347 0.6034 0.9712
7.250 0.8862 0.01765 0.01188 -0.0362 0.5771 0.9711
7.500 0.9152 0.01725 0.01105 -0.0358 0.5110 0.9720
7.750 0.9291 0.01798 0.01159 -0.0344 0.4691 0.9750
8.000 0.9350 0.01914 0.01249 -0.0322 0.4192 0.9795
8.250 0.9358 0.02060 0.01366 -0.0296 0.3624 0.9860
8.500 0.9268 0.02249 0.01513 -0.0258 0.2879 1.0000
8.750 0.9140 0.02457 0.01667 -0.0214 0.2015 1.0000
9.000 0.8904 0.02767 0.01886 -0.0163 0.0702 1.0000
9.250 0.8889 0.02960 0.02049 -0.0137 0.0245 1.0000
9.500 0.8984 0.03088 0.02180 -0.0123 0.0191 1.0000
9.750 0.9115 0.03192 0.02296 -0.0113 0.0177 1.0000
10.000 0.9233 0.03310 0.02426 -0.0102 0.0164 1.0000
10.250 0.9335 0.03443 0.02570 -0.0090 0.0151 1.0000
10.500 0.9428 0.03584 0.02722 -0.0079 0.0142 1.0000
10.750 0.9461 0.03777 0.02925 -0.0063 0.0130 1.0000
11.000 0.9548 0.03932 0.03093 -0.0053 0.0121 1.0000
11.250 0.9615 0.04107 0.03279 -0.0041 0.0117 1.0000
11.500 0.9682 0.04287 0.03469 -0.0031 0.0112 1.0000
11.750 0.9750 0.04471 0.03662 -0.0020 0.0109 1.0000
12.000 0.9818 0.04659 0.03859 -0.0010 0.0105 1.0000
12.250 0.9896 0.04843 0.04051 -0.0001 0.0102 1.0000
12.500 0.9987 0.05019 0.04236 0.0008 0.0099 1.0000
12.750 1.0091 0.05190 0.04414 0.0015 0.0096 1.0000
13.000 1.0208 0.05353 0.04585 0.0021 0.0094 1.0000
13.250 1.0325 0.05524 0.04762 0.0027 0.0090 1.0000
13.500 1.0463 0.05702 0.04947 0.0034 0.0082 1.0000
13.750 1.0589 0.05879 0.05141 0.0039 0.0081 1.0000
14.000 1.0676 0.06085 0.05368 0.0043 0.0076 1.0000
14.250 1.0786 0.06300 0.05602 0.0048 0.0075 1.0000
14.500 1.0863 0.06548 0.05872 0.0053 0.0073 1.0000
14.750 1.0910 0.06833 0.06181 0.0058 0.0072 1.0000
15.000 1.0927 0.07154 0.06525 0.0061 0.0071 1.0000
15.250 1.0916 0.07504 0.06899 0.0063 0.0070 1.0000
15.500 1.0877 0.07895 0.07315 0.0063 0.0070 1.0000
15.750 1.0804 0.08333 0.07778 0.0060 0.0069 1.0000
16.000 1.0718 0.08796 0.08265 0.0054 0.0069 1.0000
16.250 1.0614 0.09299 0.08792 0.0043 0.0069 1.0000
16.500 1.0487 0.09854 0.09371 0.0027 0.0068 1.0000
16.750 1.0357 0.10434 0.09973 0.0007 0.0069 1.0000
17.000 1.0210 0.11067 0.10627 -0.0019 0.0069 1.0000
17.250 1.0057 0.11741 0.11321 -0.0050 0.0070 1.0000
17.500 0.9894 0.12473 0.12072 -0.0088 0.0070 1.0000
17.750 0.9725 0.13256 0.12874 -0.0133 0.0070 1.0000
18.000 0.9554 0.14097 0.13732 -0.0183 0.0071 1.0000
18.250 0.9375 0.15018 0.14668 -0.0240 0.0072 1.0000
18.500 0.9205 0.15994 0.15656 -0.0301 0.0073 1.0000
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