AH 82-150 A (ah82150a-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: AH 82-150 A (ah82150a-il) Reynolds number: 200,000 Max Cl/Cd: 73.36 at α=6.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-ah82150a-il-200000-n5.txt Download as CSV file: xf-ah82150a-il-200000-n5.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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.750 -0.2786 0.09293 0.08918 -0.0901 0.9169 0.0171
-11.500 -0.2925 0.08181 0.07807 -0.0980 0.9072 0.0176
-11.000 -0.3426 0.05715 0.05317 -0.1180 0.8853 0.0171
-10.750 -0.3690 0.05087 0.04665 -0.1214 0.8735 0.0170
-10.500 -0.3920 0.04641 0.04193 -0.1216 0.8632 0.0169
-10.250 -0.4179 0.04219 0.03736 -0.1199 0.8543 0.0171
-10.000 -0.4397 0.03906 0.03390 -0.1164 0.8459 0.0173
-9.750 -0.4511 0.03608 0.03050 -0.1133 0.8400 0.0175
-9.500 -0.4547 0.03329 0.02729 -0.1106 0.8337 0.0178
-9.250 -0.4480 0.03123 0.02498 -0.1089 0.8290 0.0182
-9.000 -0.4348 0.02994 0.02351 -0.1078 0.8251 0.0187
-8.750 -0.4202 0.02871 0.02210 -0.1066 0.8207 0.0193
-8.500 -0.4038 0.02743 0.02058 -0.1056 0.8168 0.0201
-8.250 -0.3857 0.02607 0.01895 -0.1047 0.8135 0.0211
-8.000 -0.3658 0.02493 0.01752 -0.1040 0.8100 0.0227
-7.750 -0.3451 0.02390 0.01622 -0.1032 0.8061 0.0240
-7.500 -0.3242 0.02271 0.01494 -0.1027 0.8027 0.0254
-7.250 -0.3015 0.02195 0.01408 -0.1022 0.7999 0.0267
-7.000 -0.2778 0.02124 0.01323 -0.1019 0.7974 0.0284
-6.750 -0.2549 0.02065 0.01251 -0.1014 0.7938 0.0307
-6.500 -0.2314 0.01998 0.01168 -0.1008 0.7903 0.0323
-6.250 -0.2093 0.01904 0.01072 -0.1003 0.7873 0.0343
-6.000 -0.1857 0.01853 0.01016 -0.0999 0.7848 0.0366
-5.750 -0.1613 0.01810 0.00964 -0.0996 0.7825 0.0397
-5.500 -0.1386 0.01768 0.00914 -0.0990 0.7790 0.0419
-5.250 -0.1174 0.01704 0.00848 -0.0982 0.7756 0.0445
-5.000 -0.0941 0.01663 0.00805 -0.0978 0.7728 0.0483
-4.750 -0.0697 0.01628 0.00762 -0.0975 0.7703 0.0524
-4.500 -0.0454 0.01587 0.00714 -0.0972 0.7681 0.0565
-4.250 -0.0227 0.01553 0.00681 -0.0967 0.7647 0.0623
-4.000 0.0012 0.01523 0.00650 -0.0963 0.7615 0.0714
-3.750 0.0256 0.01489 0.00620 -0.0961 0.7588 0.0874
-3.500 0.0500 0.01447 0.00590 -0.0960 0.7563 0.1220
-3.250 0.0734 0.01383 0.00559 -0.0959 0.7541 0.2121
-3.000 0.0935 0.01299 0.00534 -0.0956 0.7509 0.3581
-2.750 0.1088 0.01227 0.00576 -0.0934 0.7477 0.6069
-2.500 0.1344 0.01254 0.00607 -0.0926 0.7449 0.6768
-2.250 0.1618 0.01277 0.00620 -0.0924 0.7424 0.7054
-2.000 0.1879 0.01318 0.00655 -0.0915 0.7402 0.7320
-1.750 0.2109 0.01371 0.00708 -0.0897 0.7377 0.7551
-1.500 0.2328 0.01408 0.00745 -0.0880 0.7343 0.7673
-1.250 0.2569 0.01428 0.00762 -0.0870 0.7312 0.7763
-1.000 0.2833 0.01436 0.00764 -0.0867 0.7286 0.7824
-0.750 0.3130 0.01431 0.00748 -0.0875 0.7263 0.7856
-0.500 0.3413 0.01428 0.00737 -0.0878 0.7239 0.7874
-0.250 0.3663 0.01431 0.00740 -0.0876 0.7201 0.7889
0.000 0.3931 0.01431 0.00737 -0.0876 0.7168 0.7904
0.250 0.4212 0.01428 0.00730 -0.0880 0.7139 0.7920
0.500 0.4506 0.01424 0.00719 -0.0886 0.7114 0.7934
0.750 0.4776 0.01425 0.00719 -0.0887 0.7079 0.7952
1.000 0.5040 0.01427 0.00720 -0.0889 0.7036 0.7971
1.250 0.5328 0.01423 0.00713 -0.0894 0.7000 0.7986
1.500 0.5632 0.01417 0.00701 -0.0902 0.6970 0.8001
1.750 0.5892 0.01420 0.00707 -0.0902 0.6925 0.8016
2.000 0.6149 0.01421 0.00711 -0.0901 0.6879 0.8028
2.250 0.6432 0.01418 0.00707 -0.0904 0.6842 0.8040
2.500 0.6717 0.01416 0.00705 -0.0908 0.6808 0.8051
2.750 0.6961 0.01423 0.00720 -0.0904 0.6755 0.8064
3.000 0.7236 0.01423 0.00722 -0.0907 0.6713 0.8077
3.250 0.7531 0.01420 0.00718 -0.0912 0.6678 0.8092
3.500 0.7773 0.01429 0.00737 -0.0909 0.6622 0.8111
3.750 0.8045 0.01431 0.00743 -0.0911 0.6572 0.8128
4.000 0.8344 0.01428 0.00739 -0.0917 0.6533 0.8142
4.250 0.8579 0.01439 0.00761 -0.0913 0.6466 0.8157
4.500 0.8844 0.01439 0.00768 -0.0913 0.6413 0.8168
4.750 0.9097 0.01444 0.00781 -0.0910 0.6355 0.8181
5.000 0.9342 0.01449 0.00795 -0.0907 0.6288 0.8195
5.250 0.9605 0.01452 0.00806 -0.0906 0.6227 0.8211
5.500 0.9839 0.01461 0.00825 -0.0900 0.6148 0.8230
5.750 1.0091 0.01466 0.00838 -0.0898 0.6072 0.8250
6.000 1.0338 0.01472 0.00852 -0.0894 0.5983 0.8268
6.250 1.0568 0.01483 0.00875 -0.0888 0.5883 0.8287
6.500 1.0785 0.01489 0.00887 -0.0878 0.5740 0.8305
6.750 1.0945 0.01492 0.00886 -0.0856 0.5460 0.8322
7.000 1.1039 0.01517 0.00892 -0.0822 0.5022 0.8344
7.250 1.1045 0.01571 0.00920 -0.0774 0.4554 0.8371
7.500 1.1012 0.01654 0.00978 -0.0723 0.4119 0.8405
8.000 1.0880 0.01897 0.01174 -0.0625 0.3222 0.8476
8.250 1.0792 0.02057 0.01310 -0.0580 0.2704 0.8514
8.500 1.0683 0.02257 0.01475 -0.0538 0.2104 0.8554
8.750 1.0558 0.02494 0.01670 -0.0499 0.1424 0.8593
9.000 1.0472 0.02722 0.01864 -0.0466 0.0858 0.8628
9.250 1.0415 0.02947 0.02061 -0.0439 0.0398 0.8669
9.500 1.0450 0.03119 0.02227 -0.0420 0.0261 0.8710
9.750 1.0523 0.03264 0.02380 -0.0405 0.0219 0.8751
10.000 1.0605 0.03403 0.02530 -0.0392 0.0198 0.8801
10.250 1.0669 0.03562 0.02699 -0.0378 0.0180 0.8861
10.500 1.0720 0.03728 0.02878 -0.0363 0.0169 0.8930
11.000 1.0866 0.04032 0.03213 -0.0339 0.0148 0.9144
11.500 1.0961 0.04394 0.03603 -0.0319 0.0137 1.0000
11.750 1.1013 0.04613 0.03830 -0.0313 0.0132 1.0000
12.000 1.1045 0.04855 0.04081 -0.0307 0.0128 1.0000
12.250 1.1069 0.05112 0.04345 -0.0301 0.0125 1.0000
12.500 1.1091 0.05374 0.04612 -0.0295 0.0122 1.0000
12.750 1.1164 0.05590 0.04838 -0.0291 0.0119 1.0000
13.000 1.1244 0.05801 0.05062 -0.0287 0.0116 1.0000
13.250 1.1329 0.06011 0.05282 -0.0285 0.0111 1.0000
13.500 1.1413 0.06223 0.05504 -0.0282 0.0107 1.0000
13.750 1.1493 0.06442 0.05733 -0.0281 0.0102 1.0000
14.000 1.1575 0.06664 0.05964 -0.0280 0.0099 1.0000
14.250 1.1650 0.06897 0.06206 -0.0279 0.0095 1.0000
14.500 1.1729 0.07130 0.06449 -0.0278 0.0093 1.0000
14.750 1.1802 0.07372 0.06700 -0.0277 0.0091 1.0000
15.000 1.1876 0.07621 0.06958 -0.0277 0.0089 1.0000
15.250 1.1952 0.07879 0.07227 -0.0275 0.0087 1.0000
15.500 1.2016 0.08172 0.07536 -0.0274 0.0086 1.0000
15.750 1.2030 0.08514 0.07900 -0.0278 0.0085 1.0000
16.000 1.2023 0.08892 0.08301 -0.0285 0.0084 1.0000
16.250 1.1993 0.09310 0.08742 -0.0294 0.0084 1.0000
16.500 1.1948 0.09758 0.09212 -0.0306 0.0083 1.0000
16.750 1.1880 0.10251 0.09729 -0.0322 0.0083 1.0000
17.000 1.1797 0.10779 0.10279 -0.0341 0.0082 1.0000
17.250 1.1700 0.11343 0.10866 -0.0365 0.0082 1.0000
17.500 1.1591 0.11949 0.11494 -0.0393 0.0082 1.0000
17.750 1.1472 0.12592 0.12158 -0.0426 0.0082 1.0000
18.000 1.1343 0.13280 0.12867 -0.0465 0.0082 1.0000
18.250 1.1208 0.14005 0.13612 -0.0508 0.0082 1.0000
18.500 1.1071 0.14766 0.14391 -0.0555 0.0083 1.0000
18.750 1.0929 0.15573 0.15215 -0.0607 0.0083 1.0000
19.000 1.0780 0.16445 0.16102 -0.0665 0.0083 1.0000
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Polar data table (+)
Polar graphs
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