12% JOUKOWSKI AIRFOIL (joukowsk-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: 12% JOUKOWSKI AIRFOIL (joukowsk-il) Reynolds number: 1,000,000 Max Cl/Cd: 80.44 at α=7.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-joukowsk-il-1000000.txt Download as CSV file: xf-joukowsk-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: 12% JOUKOWSKI AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-18.000 -1.2810 0.09518 0.09189 0.0106 1.0000 0.0160
-17.750 -1.2977 0.08808 0.08468 0.0064 1.0000 0.0161
-17.500 -1.3135 0.08141 0.07789 0.0026 1.0000 0.0161
-17.250 -1.3270 0.07521 0.07157 -0.0010 1.0000 0.0162
-17.000 -1.3426 0.06901 0.06526 -0.0045 1.0000 0.0162
-16.750 -1.3582 0.06300 0.05913 -0.0078 1.0000 0.0163
-16.500 -1.3807 0.05620 0.05220 -0.0115 1.0000 0.0164
-16.250 -1.4001 0.05007 0.04594 -0.0148 1.0000 0.0166
-16.000 -1.4123 0.04514 0.04090 -0.0172 1.0000 0.0168
-15.750 -1.4235 0.04059 0.03624 -0.0193 1.0000 0.0170
-15.500 -1.4282 0.03709 0.03264 -0.0206 1.0000 0.0172
-15.250 -1.4315 0.03400 0.02947 -0.0214 1.0000 0.0174
-15.000 -1.4302 0.03164 0.02702 -0.0217 1.0000 0.0177
-14.750 -1.4294 0.02947 0.02476 -0.0215 1.0000 0.0179
-14.500 -1.4257 0.02779 0.02300 -0.0209 1.0000 0.0182
-14.250 -1.4229 0.02628 0.02141 -0.0196 1.0000 0.0185
-14.000 -1.4184 0.02511 0.02017 -0.0179 1.0000 0.0189
-13.750 -1.4121 0.02419 0.01917 -0.0157 1.0000 0.0192
-13.500 -1.3992 0.02343 0.01834 -0.0142 1.0000 0.0195
-13.250 -1.3886 0.02227 0.01710 -0.0127 1.0000 0.0200
-13.000 -1.3748 0.02123 0.01602 -0.0115 1.0000 0.0207
-12.750 -1.3562 0.02051 0.01526 -0.0106 1.0000 0.0213
-12.500 -1.3359 0.01989 0.01460 -0.0099 1.0000 0.0220
-12.250 -1.3147 0.01931 0.01397 -0.0093 1.0000 0.0227
-12.000 -1.2924 0.01879 0.01339 -0.0087 1.0000 0.0232
-11.750 -1.2730 0.01791 0.01246 -0.0079 1.0000 0.0242
-11.500 -1.2509 0.01726 0.01179 -0.0074 1.0000 0.0252
-11.250 -1.2275 0.01675 0.01124 -0.0069 1.0000 0.0262
-11.000 -1.2032 0.01630 0.01075 -0.0065 1.0000 0.0271
-10.750 -1.1793 0.01578 0.01018 -0.0061 1.0000 0.0281
-10.500 -1.1559 0.01517 0.00957 -0.0057 1.0000 0.0298
-10.250 -1.1310 0.01474 0.00913 -0.0053 1.0000 0.0312
-10.000 -1.1054 0.01438 0.00873 -0.0050 1.0000 0.0323
-9.750 -1.0810 0.01381 0.00815 -0.0047 1.0000 0.0344
-9.500 -1.0554 0.01340 0.00774 -0.0044 1.0000 0.0364
-9.250 -1.0289 0.01309 0.00741 -0.0042 1.0000 0.0380
-9.000 -1.0035 0.01259 0.00691 -0.0039 1.0000 0.0409
-8.750 -0.9771 0.01224 0.00656 -0.0037 1.0000 0.0434
-8.500 -0.9506 0.01187 0.00619 -0.0035 1.0000 0.0463
-8.250 -0.9242 0.01150 0.00583 -0.0033 1.0000 0.0500
-8.000 -0.8973 0.01118 0.00551 -0.0032 1.0000 0.0537
-7.750 -0.8705 0.01082 0.00519 -0.0030 1.0000 0.0584
-7.500 -0.8434 0.01051 0.00489 -0.0029 1.0000 0.0632
-7.250 -0.8162 0.01020 0.00461 -0.0027 1.0000 0.0690
-7.000 -0.7891 0.00987 0.00433 -0.0026 1.0000 0.0761
-6.750 -0.7616 0.00959 0.00408 -0.0025 1.0000 0.0833
-6.500 -0.7341 0.00931 0.00384 -0.0024 1.0000 0.0917
-6.250 -0.7067 0.00900 0.00360 -0.0024 1.0000 0.1019
-6.000 -0.6791 0.00872 0.00338 -0.0023 1.0000 0.1127
-5.750 -0.6514 0.00846 0.00318 -0.0022 1.0000 0.1246
-5.500 -0.6150 0.00820 0.00299 -0.0040 0.9721 0.1388
-5.250 -0.5857 0.00802 0.00283 -0.0041 0.9400 0.1534
-5.000 -0.5616 0.00788 0.00267 -0.0031 0.9102 0.1677
-4.750 -0.5361 0.00772 0.00251 -0.0023 0.8847 0.1829
-4.500 -0.5099 0.00758 0.00236 -0.0018 0.8614 0.1990
-4.250 -0.4828 0.00744 0.00221 -0.0014 0.8399 0.2159
-4.000 -0.4554 0.00730 0.00208 -0.0012 0.8189 0.2335
-3.750 -0.4277 0.00718 0.00195 -0.0009 0.7988 0.2515
-3.500 -0.3998 0.00706 0.00183 -0.0008 0.7792 0.2694
-3.250 -0.3718 0.00696 0.00172 -0.0006 0.7601 0.2875
-2.750 -0.3153 0.00675 0.00153 -0.0004 0.7231 0.3255
-2.500 -0.2869 0.00666 0.00145 -0.0003 0.7049 0.3442
-2.250 -0.2584 0.00658 0.00138 -0.0003 0.6869 0.3631
-2.000 -0.2298 0.00652 0.00132 -0.0002 0.6690 0.3817
-1.750 -0.2012 0.00646 0.00127 -0.0002 0.6513 0.4001
-1.250 -0.1438 0.00636 0.00118 -0.0001 0.6157 0.4366
-1.000 -0.1151 0.00632 0.00115 -0.0001 0.5982 0.4550
-0.750 -0.0863 0.00630 0.00112 -0.0001 0.5804 0.4730
-0.500 -0.0576 0.00627 0.00110 0.0000 0.5627 0.4912
-0.250 -0.0288 0.00626 0.00109 0.0000 0.5450 0.5093
0.000 0.0000 0.00626 0.00109 0.0000 0.5270 0.5270
0.250 0.0288 0.00626 0.00109 0.0000 0.5093 0.5449
0.500 0.0575 0.00627 0.00110 0.0000 0.4911 0.5627
0.750 0.0863 0.00630 0.00112 0.0001 0.4730 0.5803
1.000 0.1150 0.00632 0.00115 0.0001 0.4549 0.5982
1.250 0.1438 0.00636 0.00118 0.0001 0.4367 0.6157
1.750 0.2011 0.00646 0.00127 0.0002 0.4002 0.6513
2.000 0.2297 0.00652 0.00132 0.0002 0.3818 0.6690
2.250 0.2583 0.00658 0.00138 0.0003 0.3631 0.6869
2.500 0.2868 0.00666 0.00145 0.0004 0.3441 0.7049
2.750 0.3153 0.00675 0.00153 0.0004 0.3253 0.7231
3.250 0.3717 0.00695 0.00172 0.0006 0.2876 0.7601
3.500 0.3998 0.00706 0.00183 0.0008 0.2694 0.7792
3.750 0.4277 0.00718 0.00195 0.0010 0.2515 0.7988
4.000 0.4554 0.00730 0.00208 0.0012 0.2335 0.8189
4.250 0.4828 0.00744 0.00221 0.0014 0.2160 0.8399
4.500 0.5098 0.00758 0.00236 0.0018 0.1991 0.8614
4.750 0.5361 0.00772 0.00251 0.0023 0.1830 0.8847
5.000 0.5615 0.00787 0.00267 0.0031 0.1677 0.9103
5.250 0.5857 0.00802 0.00283 0.0041 0.1535 0.9402
5.500 0.6150 0.00820 0.00299 0.0040 0.1389 0.9721
5.750 0.6514 0.00846 0.00318 0.0022 0.1245 1.0000
6.000 0.6791 0.00872 0.00338 0.0023 0.1128 1.0000
6.250 0.7066 0.00900 0.00360 0.0024 0.1019 1.0000
6.500 0.7341 0.00931 0.00384 0.0025 0.0917 1.0000
6.750 0.7615 0.00959 0.00408 0.0025 0.0832 1.0000
7.000 0.7890 0.00987 0.00433 0.0026 0.0761 1.0000
7.250 0.8162 0.01020 0.00461 0.0028 0.0690 1.0000
7.500 0.8433 0.01051 0.00489 0.0029 0.0632 1.0000
7.750 0.8704 0.01082 0.00519 0.0030 0.0584 1.0000
8.000 0.8972 0.01118 0.00551 0.0032 0.0537 1.0000
8.250 0.9241 0.01149 0.00583 0.0033 0.0500 1.0000
8.500 0.9506 0.01187 0.00618 0.0035 0.0463 1.0000
8.750 0.9770 0.01224 0.00656 0.0037 0.0434 1.0000
9.000 1.0034 0.01259 0.00691 0.0039 0.0409 1.0000
9.250 1.0288 0.01309 0.00740 0.0042 0.0380 1.0000
9.500 1.0552 0.01339 0.00773 0.0044 0.0364 1.0000
9.750 1.0808 0.01381 0.00815 0.0047 0.0344 1.0000
10.000 1.1053 0.01438 0.00873 0.0051 0.0323 1.0000
10.250 1.1310 0.01474 0.00913 0.0053 0.0312 1.0000
10.500 1.1560 0.01516 0.00957 0.0057 0.0297 1.0000
10.750 1.1794 0.01579 0.01019 0.0061 0.0281 1.0000
11.000 1.2034 0.01630 0.01075 0.0065 0.0271 1.0000
11.250 1.2276 0.01674 0.01124 0.0069 0.0261 1.0000
11.500 1.2509 0.01726 0.01178 0.0074 0.0252 1.0000
11.750 1.2727 0.01792 0.01246 0.0080 0.0242 1.0000
12.000 1.2923 0.01878 0.01338 0.0087 0.0232 1.0000
12.250 1.3145 0.01930 0.01395 0.0093 0.0227 1.0000
12.500 1.3356 0.01988 0.01458 0.0100 0.0220 1.0000
12.750 1.3558 0.02050 0.01525 0.0107 0.0213 1.0000
13.000 1.3742 0.02123 0.01602 0.0116 0.0207 1.0000
13.250 1.3878 0.02228 0.01711 0.0128 0.0200 1.0000
13.500 1.3982 0.02344 0.01835 0.0144 0.0195 1.0000
13.750 1.4110 0.02418 0.01917 0.0159 0.0192 1.0000
14.000 1.4174 0.02510 0.02016 0.0180 0.0189 1.0000
14.250 1.4214 0.02631 0.02144 0.0198 0.0185 1.0000
14.500 1.4256 0.02773 0.02294 0.0210 0.0182 1.0000
14.750 1.4280 0.02950 0.02480 0.0217 0.0179 1.0000
15.000 1.4300 0.03157 0.02695 0.0218 0.0177 1.0000
15.250 1.4307 0.03400 0.02946 0.0215 0.0174 1.0000
15.500 1.4283 0.03698 0.03253 0.0207 0.0172 1.0000
15.750 1.4221 0.04064 0.03629 0.0194 0.0170 1.0000
16.000 1.4121 0.04504 0.04080 0.0174 0.0168 1.0000
16.250 1.3984 0.05017 0.04605 0.0148 0.0166 1.0000
16.500 1.3813 0.05598 0.05197 0.0118 0.0164 1.0000
16.750 1.3571 0.06298 0.05911 0.0079 0.0163 1.0000
17.000 1.3414 0.06901 0.06526 0.0046 0.0163 1.0000
17.250 1.3267 0.07506 0.07143 0.0012 0.0162 1.0000
17.500 1.3129 0.08131 0.07780 -0.0024 0.0161 1.0000
17.750 1.2970 0.08799 0.08459 -0.0063 0.0161 1.0000
18.000 1.2812 0.09492 0.09163 -0.0104 0.0160 1.0000
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