AH 80-129 (ah80129-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: AH 80-129 (ah80129-il) Reynolds number: 200,000 Max Cl/Cd: 78.41 at α=6.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-ah80129-il-200000-n5.txt Download as CSV file: xf-ah80129-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: AH 80-129
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
------ -------- --------- --------- -------- -------- --------
-10.250 -0.1860 0.09544 0.09123 -0.0833 0.8224 0.0153
-10.000 -0.1848 0.09115 0.08695 -0.0852 0.8205 0.0151
-9.750 -0.1810 0.08793 0.08376 -0.0867 0.8180 0.0147
-9.250 -0.1788 0.08055 0.07642 -0.0900 0.8125 0.0131
-9.000 -0.1792 0.07678 0.07268 -0.0921 0.8096 0.0139
-8.750 -0.1821 0.07263 0.06853 -0.0942 0.8072 0.0126
-8.500 -0.1879 0.06842 0.06439 -0.0969 0.8039 0.0126
-8.250 -0.1956 0.06459 0.06058 -0.0995 0.7999 0.0130
-8.000 -0.2191 0.05909 0.05503 -0.0998 0.7962 0.0114
-7.750 -0.2330 0.05210 0.04785 -0.0997 0.7935 0.0102
-7.500 -0.2210 0.05339 0.04916 -0.0991 0.7906 0.0148
-7.250 -0.2239 0.05002 0.04568 -0.0979 0.7872 0.0138
-7.000 -0.2232 0.04648 0.04195 -0.0965 0.7842 0.0138
-6.750 -0.2213 0.04259 0.03779 -0.0945 0.7816 0.0140
-6.500 -0.2184 0.03853 0.03339 -0.0921 0.7795 0.0136
-6.250 -0.2121 0.03510 0.02965 -0.0897 0.7761 0.0132
-6.000 -0.2035 0.03167 0.02582 -0.0870 0.7729 0.0128
-5.750 -0.1919 0.02845 0.02212 -0.0844 0.7702 0.0127
-5.500 -0.1760 0.02587 0.01906 -0.0823 0.7681 0.0126
-5.250 -0.1565 0.02373 0.01644 -0.0807 0.7663 0.0125
-5.000 -0.1354 0.02202 0.01439 -0.0794 0.7633 0.0127
-4.750 -0.1129 0.02062 0.01275 -0.0784 0.7602 0.0132
-4.500 -0.0893 0.01950 0.01142 -0.0776 0.7575 0.0137
-4.250 -0.0655 0.01850 0.01025 -0.0768 0.7553 0.0146
-4.000 -0.0415 0.01772 0.00932 -0.0760 0.7534 0.0158
-3.750 -0.0188 0.01705 0.00855 -0.0751 0.7510 0.0171
-3.500 0.0023 0.01648 0.00792 -0.0741 0.7474 0.0207
-3.250 0.0253 0.01605 0.00740 -0.0732 0.7444 0.0223
-3.000 0.0486 0.01556 0.00679 -0.0722 0.7420 0.0271
-2.750 0.0721 0.01508 0.00632 -0.0714 0.7400 0.0447
-2.500 0.0959 0.01476 0.00604 -0.0708 0.7378 0.0717
-2.250 0.1145 0.01425 0.00595 -0.0695 0.7337 0.1560
-2.000 0.1307 0.01349 0.00576 -0.0678 0.7306 0.3143
-1.750 0.1453 0.01275 0.00558 -0.0654 0.7281 0.4821
-1.500 0.1593 0.01191 0.00552 -0.0623 0.7261 0.6990
-1.250 0.2081 0.01174 0.00565 -0.0660 0.7243 0.8576
-1.000 0.2535 0.01190 0.00578 -0.0695 0.7208 0.9026
-0.750 0.3111 0.01213 0.00588 -0.0753 0.7184 0.9392
-0.500 0.3592 0.01226 0.00589 -0.0794 0.7160 0.9533
-0.250 0.4081 0.01233 0.00582 -0.0838 0.7141 0.9630
0.000 0.4464 0.01232 0.00571 -0.0861 0.7121 0.9707
0.250 0.4838 0.01238 0.00573 -0.0886 0.7086 0.9759
0.500 0.5153 0.01244 0.00575 -0.0898 0.7049 0.9815
0.750 0.5510 0.01240 0.00566 -0.0918 0.7020 0.9849
1.000 0.5849 0.01235 0.00555 -0.0934 0.6995 0.9887
1.250 0.6186 0.01234 0.00551 -0.0951 0.6965 0.9922
1.500 0.6513 0.01241 0.00562 -0.0967 0.6923 0.9958
1.750 0.6843 0.01240 0.00560 -0.0982 0.6888 0.9991
2.000 0.7111 0.01236 0.00553 -0.0983 0.6860 1.0000
2.250 0.7322 0.01241 0.00559 -0.0974 0.6822 1.0000
2.500 0.7523 0.01250 0.00575 -0.0962 0.6774 1.0000
2.750 0.7744 0.01251 0.00577 -0.0954 0.6739 1.0000
3.000 0.7977 0.01250 0.00574 -0.0946 0.6712 1.0000
3.250 0.8161 0.01267 0.00600 -0.0932 0.6657 1.0000
3.500 0.8374 0.01273 0.00608 -0.0922 0.6613 1.0000
3.750 0.8608 0.01270 0.00607 -0.0915 0.6579 1.0000
4.000 0.8792 0.01289 0.00638 -0.0900 0.6522 1.0000
4.250 0.9005 0.01295 0.00649 -0.0889 0.6473 1.0000
4.500 0.9243 0.01294 0.00651 -0.0883 0.6436 1.0000
4.750 0.9418 0.01318 0.00686 -0.0867 0.6375 1.0000
5.000 0.9637 0.01326 0.00700 -0.0857 0.6328 1.0000
5.250 0.9851 0.01336 0.00722 -0.0846 0.6275 1.0000
5.500 1.0045 0.01353 0.00749 -0.0833 0.6211 1.0000
5.750 1.0287 0.01355 0.00758 -0.0827 0.6166 1.0000
6.000 1.0457 0.01382 0.00801 -0.0809 0.6094 1.0000
6.250 1.0656 0.01385 0.00812 -0.0794 0.5982 1.0000
6.500 1.0797 0.01377 0.00800 -0.0765 0.5691 1.0000
6.750 1.0831 0.01400 0.00791 -0.0717 0.5102 1.0000
7.000 1.0799 0.01473 0.00834 -0.0661 0.4507 1.0000
7.250 1.0521 0.01617 0.00924 -0.0568 0.3714 1.0000
7.500 1.0313 0.01799 0.01064 -0.0501 0.3047 1.0000
8.000 0.9915 0.02315 0.01471 -0.0397 0.1346 1.0000
8.250 0.9817 0.02552 0.01666 -0.0361 0.0664 1.0000
8.500 0.9749 0.02784 0.01866 -0.0331 0.0222 1.0000
8.750 0.9790 0.02949 0.02032 -0.0310 0.0130 1.0000
9.000 0.9850 0.03104 0.02197 -0.0292 0.0107 1.0000
9.250 0.9895 0.03278 0.02387 -0.0273 0.0095 1.0000
9.500 0.9965 0.03433 0.02554 -0.0258 0.0093 1.0000
9.750 1.0026 0.03598 0.02733 -0.0243 0.0091 1.0000
10.000 1.0095 0.03758 0.02903 -0.0230 0.0089 1.0000
10.250 1.0131 0.03953 0.03110 -0.0214 0.0084 1.0000
10.500 1.0192 0.04132 0.03299 -0.0200 0.0084 1.0000
10.750 1.0254 0.04314 0.03490 -0.0186 0.0076 1.0000
11.000 1.0320 0.04494 0.03686 -0.0172 0.0078 1.0000
11.250 1.0412 0.04653 0.03852 -0.0162 0.0070 1.0000
11.500 1.0511 0.04818 0.04028 -0.0143 0.0075 1.0000
11.750 1.0613 0.04978 0.04195 -0.0133 0.0067 1.0000
12.000 1.0720 0.05137 0.04363 -0.0123 0.0064 1.0000
12.250 1.0822 0.05316 0.04548 -0.0111 0.0059 1.0000
12.500 1.0936 0.05515 0.04765 -0.0097 0.0053 1.0000
12.750 1.1041 0.05716 0.04990 -0.0086 0.0050 1.0000
13.000 1.1129 0.05932 0.05223 -0.0077 0.0052 1.0000
13.250 1.1190 0.06186 0.05499 -0.0067 0.0051 1.0000
13.500 1.1215 0.06494 0.05832 -0.0056 0.0051 1.0000
13.750 1.1210 0.06823 0.06186 -0.0047 0.0052 1.0000
14.000 1.1181 0.07158 0.06545 -0.0043 0.0051 1.0000
14.250 1.1111 0.07574 0.06989 -0.0038 0.0050 1.0000
14.500 1.1041 0.07980 0.07414 -0.0038 0.0052 1.0000
14.750 1.0915 0.08484 0.07945 -0.0040 0.0051 1.0000
15.000 1.0758 0.09056 0.08545 -0.0048 0.0049 1.0000
15.250 1.0659 0.09538 0.09043 -0.0059 0.0052 1.0000
15.500 1.0515 0.10124 0.09651 -0.0077 0.0051 1.0000
15.750 1.0399 0.10675 0.10216 -0.0096 0.0053 1.0000
16.000 1.0193 0.11460 0.11027 -0.0129 0.0051 1.0000
16.250 1.0016 0.12234 0.11820 -0.0166 0.0050 1.0000
16.500 0.9889 0.12925 0.12523 -0.0202 0.0052 1.0000
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Polar data table (+)
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