J5012 12% (j5012-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: J5012 12% (j5012-il) Reynolds number: 50,000 Max Cl/Cd: 28.21 at α=4.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-j5012-il-50000-n5.txt Download as CSV file: xf-j5012-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: J5012 12%
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.500 -0.6645 0.10268 0.09477 -0.0275 1.0000 0.0639
-12.250 -0.7772 0.07862 0.07044 -0.0451 1.0000 0.0596
-12.000 -0.8027 0.07301 0.06468 -0.0470 1.0000 0.0595
-11.750 -0.8270 0.06831 0.05979 -0.0474 1.0000 0.0595
-11.500 -0.8489 0.06434 0.05560 -0.0463 1.0000 0.0595
-11.250 -0.8645 0.06098 0.05208 -0.0443 1.0000 0.0599
-11.000 -0.8712 0.05818 0.04916 -0.0421 1.0000 0.0606
-10.750 -0.8768 0.05564 0.04647 -0.0394 1.0000 0.0613
-10.500 -0.8783 0.05329 0.04398 -0.0370 1.0000 0.0626
-10.250 -0.8784 0.05106 0.04157 -0.0345 1.0000 0.0645
-10.000 -0.8780 0.04873 0.03899 -0.0318 1.0000 0.0668
-9.750 -0.8766 0.04624 0.03611 -0.0290 1.0000 0.0693
-9.500 -0.8694 0.04382 0.03334 -0.0267 1.0000 0.0716
-9.250 -0.8551 0.04195 0.03144 -0.0252 1.0000 0.0743
-9.000 -0.8430 0.04027 0.02960 -0.0233 1.0000 0.0784
-8.750 -0.8300 0.03842 0.02734 -0.0213 1.0000 0.0833
-8.500 -0.8134 0.03687 0.02591 -0.0199 1.0000 0.0880
-8.250 -0.7977 0.03540 0.02422 -0.0181 1.0000 0.0948
-8.000 -0.7818 0.03401 0.02284 -0.0165 1.0000 0.1017
-7.750 -0.7646 0.03269 0.02134 -0.0148 1.0000 0.1106
-7.500 -0.7499 0.03150 0.02020 -0.0129 1.0000 0.1203
-7.250 -0.7347 0.03031 0.01903 -0.0109 1.0000 0.1317
-7.000 -0.7204 0.02920 0.01794 -0.0089 1.0000 0.1458
-6.750 -0.7065 0.02813 0.01688 -0.0067 1.0000 0.1628
-6.500 -0.6931 0.02709 0.01592 -0.0045 1.0000 0.1840
-6.250 -0.6808 0.02608 0.01505 -0.0021 1.0000 0.2088
-6.000 -0.6689 0.02513 0.01426 0.0004 1.0000 0.2390
-5.750 -0.6576 0.02425 0.01357 0.0030 1.0000 0.2756
-5.500 -0.6464 0.02345 0.01295 0.0058 1.0000 0.3177
-5.250 -0.6352 0.02275 0.01246 0.0086 1.0000 0.3632
-5.000 -0.6233 0.02214 0.01206 0.0115 1.0000 0.4112
-4.750 -0.6106 0.02164 0.01176 0.0144 1.0000 0.4593
-4.500 -0.5966 0.02125 0.01153 0.0173 1.0000 0.5065
-4.250 -0.5814 0.02096 0.01135 0.0200 1.0000 0.5523
-4.000 -0.5648 0.02076 0.01127 0.0227 1.0000 0.5958
-3.750 -0.5466 0.02067 0.01127 0.0251 1.0000 0.6364
-3.500 -0.5285 0.02064 0.01126 0.0276 1.0000 0.6750
-3.250 -0.5071 0.02071 0.01135 0.0296 1.0000 0.7106
-3.000 -0.4843 0.02085 0.01147 0.0312 1.0000 0.7436
-2.750 -0.4598 0.02103 0.01162 0.0326 1.0000 0.7743
-2.500 -0.4339 0.02124 0.01175 0.0335 1.0000 0.8029
-2.250 -0.4045 0.02150 0.01193 0.0337 1.0000 0.8292
-2.000 -0.3698 0.02182 0.01215 0.0328 1.0000 0.8525
-1.750 -0.3347 0.02210 0.01233 0.0315 1.0000 0.8747
-1.500 -0.2978 0.02237 0.01250 0.0297 1.0000 0.8951
-1.250 -0.2531 0.02266 0.01268 0.0262 1.0000 0.9121
-1.000 -0.2089 0.02289 0.01282 0.0226 1.0000 0.9283
-0.750 -0.1657 0.02307 0.01294 0.0189 1.0000 0.9444
-0.500 -0.1187 0.02322 0.01303 0.0142 0.9978 0.9589
-0.250 -0.0605 0.02335 0.01312 0.0074 0.9889 0.9702
0.000 0.0000 0.02339 0.01314 0.0000 0.9800 0.9800
0.250 0.0605 0.02335 0.01311 -0.0073 0.9702 0.9889
0.500 0.1185 0.02322 0.01303 -0.0142 0.9590 0.9978
0.750 0.1657 0.02307 0.01293 -0.0189 0.9444 1.0000
1.000 0.2089 0.02288 0.01281 -0.0226 0.9283 1.0000
1.250 0.2531 0.02265 0.01267 -0.0262 0.9121 1.0000
1.500 0.2976 0.02237 0.01250 -0.0297 0.8951 1.0000
1.750 0.3347 0.02210 0.01232 -0.0315 0.8747 1.0000
2.000 0.3697 0.02182 0.01215 -0.0328 0.8526 1.0000
2.250 0.4045 0.02150 0.01193 -0.0337 0.8293 1.0000
2.500 0.4338 0.02124 0.01174 -0.0335 0.8029 1.0000
2.750 0.4598 0.02103 0.01161 -0.0326 0.7743 1.0000
3.000 0.4843 0.02085 0.01147 -0.0312 0.7435 1.0000
3.250 0.5071 0.02071 0.01135 -0.0296 0.7106 1.0000
3.500 0.5286 0.02063 0.01126 -0.0276 0.6753 1.0000
3.750 0.5466 0.02067 0.01126 -0.0251 0.6365 1.0000
4.000 0.5648 0.02076 0.01127 -0.0227 0.5959 1.0000
4.250 0.5814 0.02095 0.01135 -0.0200 0.5524 1.0000
4.500 0.5965 0.02125 0.01153 -0.0173 0.5066 1.0000
4.750 0.6105 0.02164 0.01175 -0.0144 0.4592 1.0000
5.000 0.6233 0.02214 0.01206 -0.0115 0.4111 1.0000
5.250 0.6352 0.02274 0.01246 -0.0086 0.3632 1.0000
5.500 0.6464 0.02345 0.01295 -0.0058 0.3173 1.0000
5.750 0.6576 0.02425 0.01357 -0.0030 0.2755 1.0000
6.000 0.6690 0.02513 0.01426 -0.0004 0.2393 1.0000
6.250 0.6808 0.02608 0.01505 0.0021 0.2088 1.0000
6.500 0.6930 0.02709 0.01592 0.0045 0.1838 1.0000
6.750 0.7065 0.02812 0.01688 0.0067 0.1629 1.0000
7.000 0.7204 0.02920 0.01794 0.0089 0.1458 1.0000
7.250 0.7348 0.03031 0.01903 0.0109 0.1317 1.0000
7.500 0.7499 0.03149 0.02020 0.0129 0.1202 1.0000
7.750 0.7646 0.03269 0.02134 0.0148 0.1106 1.0000
8.000 0.7816 0.03400 0.02283 0.0165 0.1015 1.0000
8.250 0.7975 0.03539 0.02422 0.0182 0.0946 1.0000
8.500 0.8134 0.03686 0.02590 0.0199 0.0880 1.0000
8.750 0.8300 0.03842 0.02734 0.0213 0.0833 1.0000
9.000 0.8429 0.04027 0.02961 0.0233 0.0783 1.0000
9.250 0.8552 0.04196 0.03144 0.0252 0.0743 1.0000
9.500 0.8696 0.04382 0.03333 0.0267 0.0715 1.0000
9.750 0.8758 0.04626 0.03615 0.0291 0.0690 1.0000
10.000 0.8778 0.04871 0.03896 0.0318 0.0666 1.0000
10.250 0.8785 0.05104 0.04154 0.0345 0.0644 1.0000
10.500 0.8785 0.05330 0.04399 0.0369 0.0626 1.0000
10.750 0.8774 0.05562 0.04644 0.0394 0.0612 1.0000
11.000 0.8727 0.05817 0.04912 0.0419 0.0604 1.0000
11.250 0.8657 0.06098 0.05206 0.0442 0.0598 1.0000
11.500 0.8487 0.06438 0.05565 0.0463 0.0595 1.0000
11.750 0.8278 0.06828 0.05976 0.0473 0.0595 1.0000
12.000 0.8038 0.07297 0.06464 0.0469 0.0595 1.0000
12.250 0.7774 0.07867 0.07049 0.0449 0.0596 1.0000
12.500 0.6664 0.10240 0.09448 0.0276 0.0636 1.0000
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Polar data table (+)
Polar graphs
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