NACA 23012 12% (naca23012-il) Xfoil prediction polar at RE=50,000 Ncrit=9
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Airfoil: NACA 23012 12% (naca23012-il) Reynolds number: 50,000 Max Cl/Cd: 24.18 at α=4.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-naca23012-il-50000.txt Download as CSV file: xf-naca23012-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: NACA 23012 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.750 -0.5047 0.12904 0.12168 0.0135 1.0000 0.2848
-10.500 -0.5118 0.12671 0.11943 0.0128 1.0000 0.2973
-10.250 -0.5206 0.12519 0.11797 0.0125 1.0000 0.3117
-10.000 -0.5113 0.12175 0.11455 0.0133 1.0000 0.3281
-9.750 -0.5055 0.11864 0.11148 0.0139 1.0000 0.3448
-9.500 -0.5015 0.11570 0.10859 0.0146 1.0000 0.3616
-9.250 -0.4936 0.11236 0.10528 0.0154 1.0000 0.3786
-9.000 -0.4844 0.10893 0.10188 0.0162 1.0000 0.3954
-8.750 -0.4760 0.10561 0.09859 0.0170 1.0000 0.4123
-8.500 -0.4651 0.10207 0.09508 0.0178 1.0000 0.4294
-8.250 -0.4533 0.09850 0.09154 0.0186 1.0000 0.4467
-8.000 -0.4479 0.09551 0.08859 0.0195 1.0000 0.4633
-7.750 -0.4230 0.09056 0.08361 0.0188 1.0000 0.4692
-7.250 -0.6036 0.06155 0.05448 -0.0185 1.0000 0.2082
-7.000 -0.6138 0.05457 0.04681 -0.0194 1.0000 0.1781
-6.750 -0.6098 0.04997 0.04160 -0.0180 1.0000 0.1632
-6.500 -0.5985 0.04632 0.03763 -0.0164 1.0000 0.1575
-6.250 -0.5883 0.04319 0.03383 -0.0143 1.0000 0.1524
-6.000 -0.5734 0.04118 0.03116 -0.0120 1.0000 0.1500
-5.750 -0.5544 0.03843 0.02819 -0.0106 1.0000 0.1491
-5.500 -0.5343 0.03604 0.02551 -0.0091 1.0000 0.1485
-5.250 -0.5141 0.03423 0.02329 -0.0074 1.0000 0.1499
-5.000 -0.4919 0.03189 0.02091 -0.0063 1.0000 0.1534
-4.750 -0.4682 0.03013 0.01906 -0.0052 1.0000 0.1566
-4.500 -0.4440 0.02866 0.01743 -0.0041 1.0000 0.1619
-4.250 -0.4187 0.02722 0.01591 -0.0031 1.0000 0.1689
-4.000 -0.3926 0.02590 0.01466 -0.0021 1.0000 0.1780
-3.750 -0.3673 0.02468 0.01355 -0.0012 1.0000 0.1910
-3.500 -0.3440 0.02357 0.01255 0.0000 1.0000 0.2081
-3.250 -0.3239 0.02239 0.01165 0.0013 1.0000 0.2363
-3.000 -0.3096 0.02060 0.01087 0.0033 1.0000 0.3316
-2.750 0.0002 0.02270 0.01377 -0.0271 1.0000 1.0000
-2.500 0.0063 0.02214 0.01317 -0.0255 1.0000 1.0000
-2.250 0.0088 0.02169 0.01270 -0.0233 1.0000 1.0000
-2.000 0.0071 0.02134 0.01234 -0.0203 1.0000 1.0000
-1.750 0.0008 0.02111 0.01211 -0.0166 1.0000 1.0000
-1.500 -0.0103 0.02100 0.01200 -0.0121 1.0000 1.0000
-1.250 -0.0241 0.02099 0.01198 -0.0071 1.0000 1.0000
-1.000 -0.0372 0.02110 0.01204 -0.0023 1.0000 1.0000
-0.750 -0.0466 0.02132 0.01220 0.0018 1.0000 1.0000
-0.500 -0.0514 0.02167 0.01247 0.0052 1.0000 1.0000
-0.250 -0.0521 0.02214 0.01286 0.0077 1.0000 1.0000
0.000 0.0256 0.02304 0.01364 -0.0035 0.9766 1.0000
0.250 0.1183 0.02356 0.01409 -0.0163 0.9457 1.0000
0.500 0.2113 0.02356 0.01408 -0.0283 0.9139 1.0000
0.750 0.2958 0.02306 0.01363 -0.0376 0.8807 1.0000
1.000 0.3543 0.02248 0.01305 -0.0414 0.8451 1.0000
1.250 0.3941 0.02203 0.01254 -0.0416 0.8085 1.0000
1.500 0.4231 0.02175 0.01215 -0.0398 0.7719 1.0000
1.750 0.4446 0.02177 0.01205 -0.0371 0.7331 1.0000
2.000 0.4658 0.02188 0.01199 -0.0345 0.6960 1.0000
2.250 0.4869 0.02212 0.01206 -0.0321 0.6610 1.0000
2.500 0.5080 0.02248 0.01225 -0.0299 0.6285 1.0000
2.750 0.5300 0.02287 0.01242 -0.0279 0.6001 1.0000
3.000 0.5503 0.02349 0.01294 -0.0263 0.5722 1.0000
3.250 0.5728 0.02403 0.01329 -0.0247 0.5498 1.0000
3.500 0.5932 0.02480 0.01404 -0.0233 0.5275 1.0000
3.750 0.6145 0.02557 0.01475 -0.0220 0.5083 1.0000
4.000 0.6358 0.02638 0.01551 -0.0208 0.4910 1.0000
4.250 0.6572 0.02725 0.01636 -0.0196 0.4755 1.0000
4.500 0.6789 0.02814 0.01720 -0.0184 0.4615 1.0000
4.750 0.7012 0.02900 0.01801 -0.0173 0.4483 1.0000
5.000 0.7199 0.03021 0.01937 -0.0162 0.4352 1.0000
5.250 0.7391 0.03147 0.02072 -0.0150 0.4234 1.0000
5.500 0.7619 0.03244 0.02163 -0.0140 0.4129 1.0000
5.750 0.7788 0.03394 0.02332 -0.0129 0.4018 1.0000
6.000 0.7963 0.03550 0.02502 -0.0118 0.3919 1.0000
6.250 0.8185 0.03661 0.02613 -0.0108 0.3821 1.0000
6.500 0.8291 0.03891 0.02872 -0.0095 0.3729 1.0000
6.750 0.8553 0.03981 0.02954 -0.0087 0.3641 1.0000
7.000 0.8572 0.04292 0.03306 -0.0072 0.3553 1.0000
7.250 0.8859 0.04370 0.03373 -0.0064 0.3470 1.0000
7.500 0.8761 0.04807 0.03859 -0.0049 0.3397 1.0000
7.750 0.9101 0.04830 0.03868 -0.0041 0.3306 1.0000
8.000 0.8822 0.05464 0.04549 -0.0028 0.3259 1.0000
8.250 0.8492 0.06185 0.05293 -0.0028 0.3227 1.0000
8.500 0.7811 0.07349 0.06459 -0.0062 0.3258 1.0000
8.750 0.7234 0.08559 0.07658 -0.0130 0.3341 1.0000
9.000 0.7283 0.08983 0.08086 -0.0137 0.3319 1.0000
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Polar data table (+)
Polar graphs
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