NACA 23012 12% (naca23012-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA 23012 12% (naca23012-il) Reynolds number: 500,000 Max Cl/Cd: 77.19 at α=8.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-naca23012-il-500000-n5.txt Download as CSV file: xf-naca23012-il-500000-n5.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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-14.750 -0.9736 0.07121 0.06828 -0.0262 1.0000 0.0142
-14.500 -1.0274 0.05711 0.05383 -0.0371 1.0000 0.0141
-14.250 -1.0557 0.04961 0.04604 -0.0416 1.0000 0.0141
-14.000 -1.0746 0.04445 0.04063 -0.0434 1.0000 0.0142
-13.750 -1.0874 0.04060 0.03653 -0.0434 1.0000 0.0144
-13.500 -1.0957 0.03756 0.03324 -0.0423 1.0000 0.0145
-13.250 -1.0997 0.03512 0.03057 -0.0405 1.0000 0.0147
-13.000 -1.1000 0.03314 0.02835 -0.0382 1.0000 0.0148
-12.750 -1.0973 0.03147 0.02649 -0.0357 1.0000 0.0150
-12.500 -1.0901 0.03012 0.02504 -0.0336 1.0000 0.0152
-12.250 -1.0773 0.02908 0.02393 -0.0320 1.0000 0.0154
-12.000 -1.0620 0.02823 0.02302 -0.0307 1.0000 0.0156
-11.750 -1.0457 0.02741 0.02213 -0.0294 1.0000 0.0158
-11.500 -1.0287 0.02657 0.02120 -0.0281 1.0000 0.0161
-11.250 -1.0114 0.02567 0.02020 -0.0268 1.0000 0.0164
-11.000 -0.9940 0.02470 0.01911 -0.0255 1.0000 0.0167
-10.750 -0.9762 0.02371 0.01797 -0.0242 1.0000 0.0171
-10.500 -0.9579 0.02275 0.01687 -0.0229 1.0000 0.0174
-10.250 -0.9391 0.02186 0.01584 -0.0215 1.0000 0.0177
-10.000 -0.9196 0.02108 0.01492 -0.0202 1.0000 0.0180
-9.750 -0.9013 0.02024 0.01405 -0.0188 1.0000 0.0183
-9.500 -0.8817 0.01966 0.01345 -0.0174 1.0000 0.0186
-9.250 -0.8618 0.01916 0.01291 -0.0161 1.0000 0.0190
-9.000 -0.8419 0.01867 0.01238 -0.0147 1.0000 0.0194
-8.750 -0.8223 0.01814 0.01179 -0.0132 1.0000 0.0199
-8.500 -0.8030 0.01758 0.01118 -0.0116 1.0000 0.0203
-8.250 -0.7839 0.01704 0.01056 -0.0100 1.0000 0.0207
-8.000 -0.7649 0.01654 0.00999 -0.0083 1.0000 0.0211
-7.750 -0.7367 0.01592 0.00933 -0.0086 0.9981 0.0216
-7.500 -0.7043 0.01537 0.00877 -0.0098 0.9954 0.0221
-7.250 -0.6715 0.01494 0.00833 -0.0110 0.9926 0.0228
-7.000 -0.6394 0.01450 0.00786 -0.0121 0.9888 0.0236
-6.750 -0.6061 0.01404 0.00736 -0.0133 0.9855 0.0244
-6.500 -0.5734 0.01361 0.00687 -0.0144 0.9818 0.0251
-6.250 -0.5435 0.01312 0.00640 -0.0149 0.9758 0.0259
-6.000 -0.5105 0.01274 0.00602 -0.0161 0.9711 0.0269
-5.750 -0.4812 0.01241 0.00568 -0.0163 0.9628 0.0280
-5.500 -0.4495 0.01210 0.00532 -0.0171 0.9556 0.0293
-5.250 -0.4211 0.01174 0.00497 -0.0171 0.9451 0.0306
-5.000 -0.3924 0.01145 0.00468 -0.0172 0.9339 0.0321
-4.750 -0.3643 0.01119 0.00438 -0.0170 0.9210 0.0337
-4.500 -0.3374 0.01093 0.00409 -0.0166 0.9056 0.0355
-4.250 -0.3109 0.01072 0.00386 -0.0161 0.8878 0.0380
-4.000 -0.2847 0.01055 0.00362 -0.0155 0.8673 0.0405
-3.750 -0.2591 0.01039 0.00339 -0.0148 0.8410 0.0436
-3.500 -0.2336 0.01031 0.00317 -0.0140 0.8069 0.0466
-3.250 -0.2081 0.01021 0.00297 -0.0133 0.7735 0.0507
-3.000 -0.1817 0.01014 0.00280 -0.0128 0.7466 0.0553
-2.500 -0.1289 0.00998 0.00250 -0.0119 0.6945 0.0687
-2.250 -0.1024 0.00991 0.00237 -0.0116 0.6696 0.0790
-2.000 -0.0760 0.00981 0.00224 -0.0112 0.6433 0.0961
-1.750 -0.0504 0.00961 0.00209 -0.0108 0.6167 0.1403
-1.500 -0.0301 0.00858 0.00184 -0.0098 0.5937 0.3750
-1.250 -0.0058 0.00825 0.00176 -0.0092 0.5695 0.4686
-1.000 0.0192 0.00806 0.00171 -0.0086 0.5443 0.5361
-0.750 0.0444 0.00794 0.00169 -0.0080 0.5185 0.5939
-0.500 0.0697 0.00784 0.00168 -0.0074 0.4957 0.6480
-0.250 0.0953 0.00778 0.00169 -0.0068 0.4726 0.6922
0.250 0.1458 0.00775 0.00178 -0.0054 0.4244 0.7821
0.500 0.1708 0.00776 0.00185 -0.0045 0.4029 0.8264
0.750 0.1971 0.00785 0.00192 -0.0040 0.3823 0.8499
1.000 0.2238 0.00798 0.00198 -0.0035 0.3610 0.8672
1.250 0.2507 0.00811 0.00206 -0.0032 0.3406 0.8835
1.500 0.2779 0.00825 0.00214 -0.0029 0.3233 0.8985
1.750 0.3054 0.00840 0.00223 -0.0026 0.3078 0.9123
2.000 0.3330 0.00856 0.00232 -0.0025 0.2927 0.9251
2.250 0.3620 0.00873 0.00243 -0.0026 0.2788 0.9358
2.500 0.3916 0.00889 0.00254 -0.0029 0.2672 0.9451
2.750 0.4214 0.00905 0.00265 -0.0032 0.2575 0.9540
3.000 0.4529 0.00924 0.00277 -0.0040 0.2477 0.9606
3.250 0.4840 0.00940 0.00289 -0.0046 0.2392 0.9675
3.500 0.5158 0.00958 0.00303 -0.0055 0.2320 0.9730
3.750 0.5491 0.00974 0.00317 -0.0067 0.2250 0.9774
4.000 0.5801 0.00994 0.00331 -0.0074 0.2180 0.9827
4.250 0.6149 0.01010 0.00347 -0.0090 0.2127 0.9853
4.500 0.6493 0.01028 0.00362 -0.0105 0.2063 0.9882
4.750 0.6825 0.01049 0.00379 -0.0117 0.2005 0.9916
5.000 0.7160 0.01064 0.00396 -0.0130 0.1956 0.9946
5.250 0.7503 0.01084 0.00413 -0.0146 0.1896 0.9969
5.500 0.7838 0.01105 0.00433 -0.0160 0.1844 0.9993
5.750 0.8100 0.01121 0.00450 -0.0157 0.1796 1.0000
6.000 0.8328 0.01139 0.00468 -0.0148 0.1748 1.0000
6.250 0.8554 0.01161 0.00488 -0.0138 0.1703 1.0000
6.500 0.8786 0.01177 0.00507 -0.0130 0.1659 1.0000
6.750 0.9015 0.01199 0.00527 -0.0121 0.1608 1.0000
7.000 0.9243 0.01223 0.00551 -0.0112 0.1558 1.0000
7.250 0.9476 0.01243 0.00573 -0.0104 0.1509 1.0000
7.500 0.9704 0.01268 0.00597 -0.0095 0.1454 1.0000
7.750 0.9935 0.01293 0.00623 -0.0087 0.1406 1.0000
8.000 1.0167 0.01318 0.00649 -0.0079 0.1348 1.0000
8.250 1.0396 0.01349 0.00678 -0.0071 0.1289 1.0000
8.500 1.0629 0.01377 0.00708 -0.0064 0.1225 1.0000
8.750 1.0858 0.01412 0.00741 -0.0057 0.1164 1.0000
9.000 1.1090 0.01443 0.00775 -0.0051 0.1104 1.0000
9.250 1.1316 0.01482 0.00812 -0.0043 0.1041 1.0000
9.500 1.1544 0.01520 0.00851 -0.0037 0.0974 1.0000
9.750 1.1765 0.01564 0.00894 -0.0029 0.0902 1.0000
10.000 1.1978 0.01614 0.00941 -0.0021 0.0825 1.0000
10.250 1.2193 0.01663 0.00990 -0.0013 0.0752 1.0000
10.500 1.2402 0.01715 0.01043 -0.0005 0.0691 1.0000
10.750 1.2603 0.01773 0.01100 0.0004 0.0632 1.0000
11.000 1.2804 0.01829 0.01159 0.0013 0.0579 1.0000
11.250 1.2997 0.01890 0.01221 0.0023 0.0531 1.0000
11.750 1.3356 0.02024 0.01359 0.0045 0.0441 1.0000
12.000 1.3519 0.02098 0.01436 0.0058 0.0406 1.0000
12.250 1.3676 0.02171 0.01513 0.0072 0.0374 1.0000
12.500 1.3802 0.02249 0.01595 0.0090 0.0349 1.0000
12.750 1.3919 0.02330 0.01681 0.0109 0.0325 1.0000
13.000 1.4016 0.02427 0.01784 0.0128 0.0304 1.0000
13.250 1.4121 0.02522 0.01887 0.0145 0.0286 1.0000
13.500 1.4201 0.02640 0.02010 0.0161 0.0268 1.0000
13.750 1.4274 0.02770 0.02147 0.0175 0.0254 1.0000
14.000 1.4343 0.02910 0.02297 0.0187 0.0241 1.0000
14.250 1.4387 0.03082 0.02476 0.0197 0.0229 1.0000
14.500 1.4410 0.03287 0.02691 0.0204 0.0219 1.0000
14.750 1.4442 0.03499 0.02914 0.0207 0.0211 1.0000
15.000 1.4451 0.03754 0.03180 0.0205 0.0204 1.0000
15.250 1.4431 0.04060 0.03497 0.0199 0.0197 1.0000
15.500 1.4379 0.04429 0.03879 0.0188 0.0192 1.0000
15.750 1.4290 0.04871 0.04334 0.0171 0.0188 1.0000
16.000 1.4171 0.05377 0.04853 0.0149 0.0185 1.0000
16.250 1.4035 0.05926 0.05419 0.0124 0.0182 1.0000
16.500 1.3853 0.06555 0.06064 0.0095 0.0180 1.0000
16.750 1.3629 0.07257 0.06782 0.0062 0.0179 1.0000
17.000 1.3372 0.08020 0.07560 0.0028 0.0179 1.0000
17.250 1.3104 0.08812 0.08367 -0.0008 0.0179 1.0000
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