NACA 23012 12% (naca23012-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: NACA 23012 12% (naca23012-il) Reynolds number: 500,000 Max Cl/Cd: 77.13 at α=9° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-naca23012-il-500000.txt Download as CSV file: xf-naca23012-il-500000.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 = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.750 -0.7776 0.05538 0.05236 -0.0376 1.0000 0.0249
-10.500 -0.7894 0.05231 0.04919 -0.0355 1.0000 0.0248
-10.250 -0.8005 0.04833 0.04501 -0.0336 1.0000 0.0246
-10.000 -0.8137 0.04322 0.03958 -0.0310 1.0000 0.0244
-9.750 -0.8319 0.03644 0.03223 -0.0271 1.0000 0.0244
-9.500 -0.8389 0.03138 0.02649 -0.0231 1.0000 0.0249
-9.250 -0.8333 0.02849 0.02316 -0.0200 1.0000 0.0252
-9.000 -0.8213 0.02607 0.02057 -0.0180 1.0000 0.0256
-8.750 -0.8041 0.02503 0.01948 -0.0164 1.0000 0.0260
-8.500 -0.7860 0.02424 0.01865 -0.0148 1.0000 0.0264
-8.250 -0.7685 0.02330 0.01761 -0.0130 1.0000 0.0269
-8.000 -0.7513 0.02232 0.01651 -0.0112 1.0000 0.0276
-7.750 -0.7340 0.02128 0.01530 -0.0092 1.0000 0.0283
-7.500 -0.7164 0.02030 0.01414 -0.0073 1.0000 0.0290
-7.250 -0.6982 0.01957 0.01324 -0.0053 1.0000 0.0294
-7.000 -0.6802 0.01805 0.01167 -0.0037 1.0000 0.0301
-6.750 -0.6614 0.01741 0.01103 -0.0021 1.0000 0.0307
-6.500 -0.6420 0.01689 0.01049 -0.0006 1.0000 0.0314
-6.250 -0.6055 0.01630 0.00986 -0.0025 0.9976 0.0326
-6.000 -0.5683 0.01570 0.00919 -0.0044 0.9952 0.0338
-5.750 -0.5327 0.01480 0.00823 -0.0061 0.9926 0.0349
-5.500 -0.4974 0.01408 0.00756 -0.0078 0.9889 0.0362
-5.250 -0.4597 0.01359 0.00707 -0.0099 0.9858 0.0377
-5.000 -0.4204 0.01318 0.00663 -0.0123 0.9835 0.0397
-4.750 -0.3873 0.01247 0.00594 -0.0135 0.9779 0.0418
-4.500 -0.3491 0.01203 0.00553 -0.0157 0.9741 0.0442
-4.250 -0.3112 0.01168 0.00515 -0.0176 0.9699 0.0468
-4.000 -0.2810 0.01112 0.00464 -0.0181 0.9607 0.0507
-3.750 -0.2495 0.01085 0.00435 -0.0185 0.9495 0.0546
-3.500 -0.2218 0.01038 0.00391 -0.0182 0.9346 0.0598
-3.250 -0.1946 0.01014 0.00363 -0.0177 0.9184 0.0647
-3.000 -0.1688 0.00982 0.00333 -0.0170 0.9022 0.0727
-2.750 -0.1431 0.00956 0.00306 -0.0162 0.8841 0.0825
-2.500 -0.1175 0.00930 0.00281 -0.0154 0.8644 0.0983
-2.250 -0.0970 0.00829 0.00240 -0.0142 0.8439 0.2698
-2.000 -0.0785 0.00727 0.00218 -0.0127 0.8220 0.4948
-1.750 -0.0559 0.00688 0.00209 -0.0114 0.7979 0.5942
-1.500 -0.0320 0.00667 0.00203 -0.0102 0.7742 0.6605
-1.250 -0.0077 0.00654 0.00199 -0.0092 0.7495 0.7156
-1.000 0.0170 0.00648 0.00198 -0.0081 0.7233 0.7600
-0.750 0.0419 0.00647 0.00198 -0.0071 0.6965 0.7985
-0.500 0.0669 0.00650 0.00200 -0.0060 0.6704 0.8330
-0.250 0.0923 0.00657 0.00204 -0.0051 0.6439 0.8610
0.000 0.1175 0.00668 0.00209 -0.0041 0.6163 0.8860
0.250 0.1425 0.00683 0.00216 -0.0030 0.5878 0.9100
0.500 0.1685 0.00703 0.00227 -0.0021 0.5607 0.9308
0.750 0.1960 0.00723 0.00235 -0.0016 0.5331 0.9439
1.000 0.2250 0.00743 0.00242 -0.0017 0.5037 0.9540
1.250 0.2576 0.00765 0.00249 -0.0025 0.4734 0.9609
1.500 0.2901 0.00789 0.00258 -0.0034 0.4446 0.9681
1.750 0.3256 0.00814 0.00267 -0.0050 0.4144 0.9730
2.000 0.3644 0.00840 0.00277 -0.0074 0.3834 0.9761
2.250 0.4007 0.00864 0.00288 -0.0093 0.3562 0.9807
2.500 0.4372 0.00889 0.00299 -0.0112 0.3321 0.9846
2.750 0.4758 0.00912 0.00310 -0.0136 0.3109 0.9874
3.000 0.5130 0.00934 0.00321 -0.0157 0.2936 0.9910
3.250 0.5496 0.00956 0.00335 -0.0177 0.2798 0.9944
3.500 0.5880 0.00974 0.00346 -0.0201 0.2674 0.9969
3.750 0.6260 0.00991 0.00358 -0.0224 0.2574 0.9996
4.250 0.6741 0.01021 0.00382 -0.0212 0.2428 1.0000
4.500 0.6967 0.01039 0.00396 -0.0203 0.2360 1.0000
4.750 0.7194 0.01057 0.00413 -0.0193 0.2303 1.0000
5.000 0.7423 0.01071 0.00427 -0.0184 0.2246 1.0000
5.250 0.7644 0.01095 0.00445 -0.0174 0.2186 1.0000
5.500 0.7872 0.01112 0.00465 -0.0164 0.2137 1.0000
5.750 0.8101 0.01128 0.00482 -0.0155 0.2084 1.0000
6.000 0.8320 0.01155 0.00504 -0.0145 0.2030 1.0000
6.250 0.8549 0.01174 0.00526 -0.0135 0.1983 1.0000
6.500 0.8781 0.01191 0.00545 -0.0126 0.1933 1.0000
6.750 0.9004 0.01218 0.00568 -0.0117 0.1880 1.0000
7.000 0.9234 0.01240 0.00593 -0.0108 0.1832 1.0000
7.250 0.9470 0.01257 0.00613 -0.0100 0.1780 1.0000
7.500 0.9692 0.01287 0.00639 -0.0090 0.1725 1.0000
7.750 0.9927 0.01308 0.00665 -0.0083 0.1678 1.0000
8.000 1.0163 0.01329 0.00688 -0.0076 0.1623 1.0000
8.250 1.0386 0.01364 0.00719 -0.0067 0.1564 1.0000
8.500 1.0632 0.01380 0.00743 -0.0062 0.1509 1.0000
8.750 1.0861 0.01413 0.00772 -0.0054 0.1449 1.0000
9.000 1.1099 0.01439 0.00804 -0.0048 0.1395 1.0000
9.250 1.1332 0.01470 0.00835 -0.0042 0.1332 1.0000
9.500 1.1563 0.01504 0.00871 -0.0036 0.1272 1.0000
9.750 1.1793 0.01539 0.00905 -0.0029 0.1200 1.0000
10.000 1.2021 0.01576 0.00944 -0.0023 0.1132 1.0000
10.250 1.2235 0.01624 0.00990 -0.0015 0.1056 1.0000
10.500 1.2461 0.01662 0.01032 -0.0009 0.0989 1.0000
10.750 1.2668 0.01715 0.01084 0.0000 0.0921 1.0000
11.000 1.2872 0.01769 0.01138 0.0008 0.0850 1.0000
11.250 1.3072 0.01825 0.01197 0.0018 0.0783 1.0000
11.500 1.3255 0.01892 0.01264 0.0029 0.0717 1.0000
11.750 1.3428 0.01964 0.01335 0.0041 0.0653 1.0000
12.000 1.3600 0.02034 0.01409 0.0053 0.0597 1.0000
12.250 1.3742 0.02121 0.01497 0.0068 0.0547 1.0000
12.500 1.3870 0.02203 0.01582 0.0086 0.0502 1.0000
12.750 1.3967 0.02296 0.01680 0.0108 0.0465 1.0000
13.000 1.4054 0.02399 0.01787 0.0128 0.0431 1.0000
13.250 1.4124 0.02518 0.01912 0.0149 0.0403 1.0000
13.500 1.4198 0.02641 0.02042 0.0165 0.0377 1.0000
13.750 1.4206 0.02820 0.02226 0.0183 0.0355 1.0000
14.000 1.4279 0.02964 0.02380 0.0194 0.0336 1.0000
14.250 1.4299 0.03162 0.02586 0.0203 0.0320 1.0000
14.500 1.4241 0.03455 0.02887 0.0208 0.0306 1.0000
14.750 1.4257 0.03701 0.03147 0.0208 0.0295 1.0000
15.000 1.4242 0.04001 0.03459 0.0203 0.0284 1.0000
15.250 1.4190 0.04369 0.03839 0.0192 0.0276 1.0000
15.500 1.4087 0.04829 0.04311 0.0174 0.0270 1.0000
15.750 1.3932 0.05383 0.04877 0.0150 0.0265 1.0000
16.000 1.3730 0.06022 0.05529 0.0121 0.0261 1.0000
16.250 1.3561 0.06625 0.06147 0.0094 0.0258 1.0000
16.500 1.3394 0.07231 0.06767 0.0068 0.0255 1.0000
16.750 1.3211 0.07866 0.07416 0.0040 0.0253 1.0000
17.000 1.3028 0.08512 0.08074 0.0011 0.0251 1.0000
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Polar data table (+)
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