AH 93-K-130/15 (ah93k130-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: AH 93-K-130/15 (ah93k130-il) Reynolds number: 500,000 Max Cl/Cd: 104.47 at α=5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-ah93k130-il-500000-n5.txt Download as CSV file: xf-ah93k130-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: AH 93-K-130/15
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.750 -0.4960 0.08225 0.07956 -0.0292 0.7799 0.0092
-9.250 -0.7104 0.02978 0.02522 -0.0392 0.7777 0.0094
-9.000 -0.6962 0.02767 0.02282 -0.0380 0.7767 0.0096
-8.750 -0.6758 0.02651 0.02152 -0.0374 0.7754 0.0099
-8.500 -0.6533 0.02575 0.02067 -0.0370 0.7742 0.0102
-8.250 -0.6305 0.02500 0.01980 -0.0367 0.7731 0.0105
-8.000 -0.6083 0.02401 0.01862 -0.0361 0.7719 0.0109
-7.750 -0.5867 0.02277 0.01716 -0.0354 0.7708 0.0114
-7.500 -0.5648 0.02146 0.01559 -0.0347 0.7697 0.0118
-7.250 -0.5418 0.02032 0.01422 -0.0340 0.7688 0.0122
-7.000 -0.5179 0.01940 0.01311 -0.0335 0.7679 0.0126
-6.750 -0.4941 0.01841 0.01195 -0.0329 0.7670 0.0130
-6.500 -0.4696 0.01770 0.01115 -0.0325 0.7663 0.0135
-6.250 -0.4439 0.01723 0.01060 -0.0323 0.7656 0.0140
-6.000 -0.4181 0.01677 0.01007 -0.0321 0.7649 0.0146
-5.750 -0.3922 0.01633 0.00955 -0.0318 0.7642 0.0154
-5.500 -0.3661 0.01591 0.00904 -0.0316 0.7635 0.0163
-5.250 -0.3385 0.01557 0.00865 -0.0318 0.7615 0.0171
-5.000 -0.3128 0.01496 0.00799 -0.0316 0.7596 0.0181
-4.750 -0.2861 0.01461 0.00762 -0.0316 0.7579 0.0191
-4.500 -0.2592 0.01430 0.00728 -0.0315 0.7565 0.0202
-4.250 -0.2326 0.01397 0.00691 -0.0314 0.7552 0.0215
-4.000 -0.2057 0.01369 0.00657 -0.0313 0.7541 0.0227
-3.750 -0.1796 0.01328 0.00613 -0.0311 0.7530 0.0244
-3.500 -0.1531 0.01296 0.00580 -0.0309 0.7520 0.0263
-3.250 -0.1263 0.01268 0.00548 -0.0307 0.7510 0.0280
-3.000 -0.0993 0.01243 0.00518 -0.0306 0.7501 0.0300
-2.750 -0.0718 0.01224 0.00498 -0.0307 0.7480 0.0321
-2.500 -0.0444 0.01202 0.00479 -0.0309 0.7455 0.0353
-2.250 -0.0168 0.01184 0.00461 -0.0310 0.7435 0.0386
-2.000 0.0107 0.01166 0.00440 -0.0310 0.7418 0.0425
-1.750 0.0379 0.01143 0.00420 -0.0310 0.7404 0.0496
-1.500 0.0652 0.01121 0.00400 -0.0309 0.7391 0.0590
-1.250 0.0922 0.01095 0.00379 -0.0309 0.7378 0.0787
-1.000 0.1183 0.01060 0.00359 -0.0306 0.7367 0.1263
-0.750 0.1440 0.01026 0.00356 -0.0306 0.7338 0.2109
-0.500 0.1683 0.00981 0.00352 -0.0303 0.7307 0.3306
-0.250 0.1831 0.00875 0.00336 -0.0281 0.7282 0.5930
0.250 0.2897 0.00838 0.00406 -0.0381 0.7254 0.9524
0.500 0.3384 0.00872 0.00435 -0.0421 0.7239 0.9729
0.750 0.3855 0.00876 0.00435 -0.0463 0.7216 0.9789
1.000 0.4172 0.00881 0.00440 -0.0474 0.7173 0.9816
1.250 0.4469 0.00877 0.00434 -0.0480 0.7136 0.9840
1.500 0.4802 0.00864 0.00417 -0.0494 0.7107 0.9850
1.750 0.5132 0.00859 0.00410 -0.0507 0.7065 0.9862
2.000 0.5459 0.00855 0.00407 -0.0521 0.7010 0.9874
2.250 0.5777 0.00843 0.00393 -0.0531 0.6967 0.9889
2.500 0.6093 0.00842 0.00392 -0.0542 0.6910 0.9903
2.750 0.6400 0.00837 0.00386 -0.0550 0.6852 0.9917
3.000 0.6703 0.00833 0.00382 -0.0558 0.6791 0.9931
3.250 0.7008 0.00831 0.00378 -0.0566 0.6715 0.9942
3.500 0.7329 0.00826 0.00372 -0.0578 0.6632 0.9950
3.750 0.7643 0.00823 0.00365 -0.0588 0.6539 0.9959
4.000 0.7956 0.00824 0.00364 -0.0598 0.6412 0.9968
4.250 0.8266 0.00831 0.00365 -0.0608 0.6257 0.9977
4.500 0.8573 0.00841 0.00371 -0.0618 0.6100 0.9985
4.750 0.8880 0.00856 0.00382 -0.0629 0.5927 0.9993
5.000 0.9183 0.00879 0.00397 -0.0639 0.5701 1.0000
5.250 0.9446 0.00915 0.00421 -0.0642 0.5405 1.0000
5.750 0.9948 0.01006 0.00489 -0.0647 0.4784 1.0000
6.000 1.0173 0.01072 0.00538 -0.0646 0.4381 1.0000
6.250 1.0361 0.01161 0.00602 -0.0641 0.3886 1.0000
6.500 1.0513 0.01257 0.00675 -0.0631 0.3410 1.0000
6.750 1.0628 0.01363 0.00759 -0.0614 0.2950 1.0000
7.000 1.0683 0.01481 0.00853 -0.0589 0.2504 1.0000
7.250 1.0686 0.01585 0.00940 -0.0551 0.2165 1.0000
7.500 1.0598 0.01666 0.01010 -0.0491 0.1941 1.0000
7.750 1.0572 0.01746 0.01079 -0.0444 0.1705 1.0000
8.000 1.0575 0.01829 0.01150 -0.0404 0.1471 1.0000
8.250 1.0596 0.01914 0.01223 -0.0367 0.1240 1.0000
8.500 1.0634 0.01998 0.01297 -0.0334 0.1034 1.0000
8.750 1.0685 0.02082 0.01373 -0.0304 0.0858 1.0000
9.000 1.0753 0.02162 0.01447 -0.0277 0.0721 1.0000
9.250 1.0830 0.02241 0.01522 -0.0252 0.0608 1.0000
9.500 1.0914 0.02320 0.01598 -0.0228 0.0510 1.0000
9.750 1.1001 0.02402 0.01677 -0.0206 0.0429 1.0000
10.000 1.1083 0.02489 0.01762 -0.0184 0.0360 1.0000
10.250 1.1184 0.02569 0.01843 -0.0165 0.0315 1.0000
10.500 1.1274 0.02659 0.01935 -0.0145 0.0275 1.0000
10.750 1.1379 0.02742 0.02022 -0.0127 0.0251 1.0000
11.000 1.1473 0.02835 0.02117 -0.0109 0.0226 1.0000
11.250 1.1557 0.02940 0.02223 -0.0091 0.0203 1.0000
11.500 1.1664 0.03032 0.02322 -0.0076 0.0192 1.0000
11.750 1.1768 0.03132 0.02428 -0.0062 0.0179 1.0000
12.000 1.1863 0.03245 0.02545 -0.0048 0.0167 1.0000
12.250 1.1946 0.03371 0.02674 -0.0033 0.0155 1.0000
12.500 1.2027 0.03504 0.02815 -0.0020 0.0145 1.0000
12.750 1.2129 0.03624 0.02942 -0.0009 0.0138 1.0000
13.000 1.2223 0.03755 0.03080 0.0002 0.0131 1.0000
13.250 1.2308 0.03897 0.03229 0.0013 0.0124 1.0000
13.500 1.2387 0.04047 0.03385 0.0023 0.0118 1.0000
13.750 1.2450 0.04215 0.03558 0.0033 0.0111 1.0000
14.000 1.2483 0.04418 0.03768 0.0044 0.0105 1.0000
14.250 1.2567 0.04578 0.03937 0.0051 0.0101 1.0000
14.500 1.2637 0.04753 0.04123 0.0058 0.0097 1.0000
14.750 1.2700 0.04939 0.04318 0.0065 0.0092 1.0000
15.000 1.2755 0.05137 0.04524 0.0070 0.0088 1.0000
15.250 1.2803 0.05349 0.04744 0.0075 0.0084 1.0000
15.500 1.2841 0.05575 0.04978 0.0080 0.0081 1.0000
15.750 1.2863 0.05823 0.05234 0.0083 0.0078 1.0000
16.000 1.2849 0.06119 0.05538 0.0087 0.0075 1.0000
16.250 1.2858 0.06394 0.05824 0.0088 0.0072 1.0000
16.500 1.2880 0.06661 0.06102 0.0089 0.0070 1.0000
16.750 1.2892 0.06945 0.06397 0.0088 0.0068 1.0000
17.000 1.2894 0.07245 0.06709 0.0086 0.0065 1.0000
17.250 1.2894 0.07555 0.07029 0.0083 0.0063 1.0000
17.500 1.2885 0.07883 0.07369 0.0079 0.0061 1.0000
17.750 1.2871 0.08226 0.07722 0.0073 0.0059 1.0000
18.000 1.2846 0.08588 0.08095 0.0066 0.0057 1.0000
18.250 1.2807 0.08976 0.08493 0.0057 0.0055 1.0000
18.500 1.2752 0.09395 0.08923 0.0046 0.0054 1.0000
18.750 1.2683 0.09847 0.09386 0.0033 0.0053 1.0000
19.000 1.2596 0.10335 0.09885 0.0018 0.0052 1.0000
19.250 1.2490 0.10861 0.10423 0.0000 0.0050 1.0000
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