NACA 0012 AIRFOILS (n0012-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: NACA 0012 AIRFOILS (n0012-il) Reynolds number: 500,000 Max Cl/Cd: 61.75 at α=6.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-n0012-il-500000.txt Download as CSV file: xf-n0012-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: NACA 0012 AIRFOILS
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
------ -------- --------- --------- -------- -------- --------
-17.750 -1.0298 0.12468 0.12173 0.0079 1.0000 0.0199
-17.500 -1.0693 0.11191 0.10877 0.0002 1.0000 0.0198
-17.250 -1.0995 0.10168 0.09835 -0.0060 1.0000 0.0198
-17.000 -1.1249 0.09280 0.08929 -0.0113 1.0000 0.0198
-16.750 -1.1466 0.08496 0.08127 -0.0159 1.0000 0.0198
-16.500 -1.1653 0.07799 0.07413 -0.0199 1.0000 0.0198
-16.250 -1.1812 0.07170 0.06767 -0.0235 1.0000 0.0199
-16.000 -1.1949 0.06606 0.06186 -0.0265 1.0000 0.0200
-15.750 -1.2058 0.06100 0.05662 -0.0291 1.0000 0.0201
-15.500 -1.2144 0.05648 0.05192 -0.0313 1.0000 0.0202
-15.250 -1.2215 0.05237 0.04764 -0.0331 1.0000 0.0204
-15.000 -1.2315 0.04811 0.04324 -0.0338 1.0000 0.0206
-14.750 -1.2349 0.04484 0.03986 -0.0342 1.0000 0.0209
-14.500 -1.2347 0.04212 0.03707 -0.0345 1.0000 0.0212
-14.250 -1.2325 0.03975 0.03462 -0.0345 1.0000 0.0215
-14.000 -1.2291 0.03762 0.03240 -0.0342 1.0000 0.0218
-13.750 -1.2249 0.03570 0.03037 -0.0337 1.0000 0.0222
-13.500 -1.2199 0.03394 0.02850 -0.0328 1.0000 0.0226
-13.250 -1.2139 0.03236 0.02680 -0.0316 1.0000 0.0230
-13.000 -1.2065 0.03098 0.02531 -0.0303 1.0000 0.0236
-12.750 -1.1977 0.02979 0.02397 -0.0288 1.0000 0.0240
-12.500 -1.1907 0.02837 0.02243 -0.0268 1.0000 0.0245
-12.250 -1.1850 0.02684 0.02086 -0.0246 1.0000 0.0251
-12.000 -1.1748 0.02586 0.01984 -0.0225 1.0000 0.0257
-11.750 -1.1622 0.02501 0.01893 -0.0207 1.0000 0.0264
-11.500 -1.1470 0.02416 0.01801 -0.0192 1.0000 0.0271
-11.250 -1.1306 0.02336 0.01712 -0.0178 1.0000 0.0279
-11.000 -1.1126 0.02267 0.01632 -0.0165 1.0000 0.0287
-10.750 -1.0994 0.02143 0.01504 -0.0147 1.0000 0.0297
-10.500 -1.0815 0.02069 0.01429 -0.0135 1.0000 0.0308
-10.250 -1.0618 0.02009 0.01364 -0.0124 1.0000 0.0320
-10.000 -1.0416 0.01951 0.01300 -0.0113 1.0000 0.0333
-9.750 -1.0223 0.01882 0.01223 -0.0100 1.0000 0.0344
-9.500 -1.0053 0.01794 0.01135 -0.0085 1.0000 0.0360
-9.250 -0.9846 0.01743 0.01081 -0.0074 1.0000 0.0377
-9.000 -0.9632 0.01700 0.01032 -0.0064 1.0000 0.0395
-8.750 -0.9450 0.01628 0.00958 -0.0048 1.0000 0.0416
-8.500 -0.9250 0.01577 0.00908 -0.0035 1.0000 0.0439
-8.250 -0.9040 0.01537 0.00864 -0.0023 1.0000 0.0463
-8.000 -0.8851 0.01479 0.00804 -0.0007 1.0000 0.0492
-7.750 -0.8647 0.01437 0.00763 0.0006 1.0000 0.0526
-7.500 -0.8439 0.01400 0.00722 0.0019 1.0000 0.0561
-7.250 -0.8245 0.01350 0.00677 0.0034 1.0000 0.0609
-7.000 -0.8036 0.01316 0.00640 0.0047 1.0000 0.0657
-6.750 -0.7836 0.01275 0.00603 0.0061 1.0000 0.0723
-6.500 -0.7633 0.01237 0.00568 0.0075 1.0000 0.0799
-6.250 -0.7424 0.01204 0.00537 0.0087 1.0000 0.0888
-6.000 -0.7216 0.01171 0.00509 0.0100 1.0000 0.1000
-5.750 -0.7007 0.01136 0.00482 0.0112 1.0000 0.1141
-5.500 -0.6797 0.01102 0.00458 0.0124 1.0000 0.1312
-5.250 -0.6582 0.01072 0.00437 0.0134 1.0000 0.1513
-5.000 -0.6274 0.01036 0.00414 0.0125 0.9985 0.1775
-4.750 -0.5903 0.01000 0.00393 0.0102 0.9957 0.2096
-4.500 -0.5529 0.00966 0.00374 0.0080 0.9931 0.2444
-4.250 -0.5172 0.00932 0.00354 0.0061 0.9892 0.2791
-4.000 -0.4798 0.00900 0.00338 0.0039 0.9858 0.3152
-3.750 -0.4410 0.00869 0.00322 0.0014 0.9832 0.3524
-3.500 -0.4066 0.00840 0.00307 -0.0001 0.9779 0.3872
-3.250 -0.3690 0.00813 0.00293 -0.0022 0.9740 0.4226
-3.000 -0.3306 0.00786 0.00279 -0.0044 0.9707 0.4575
-2.750 -0.2994 0.00761 0.00267 -0.0050 0.9628 0.4893
-2.500 -0.2655 0.00737 0.00254 -0.0062 0.9565 0.5214
-2.250 -0.2374 0.00715 0.00243 -0.0060 0.9458 0.5510
-2.000 -0.2089 0.00696 0.00233 -0.0059 0.9351 0.5802
-1.750 -0.1812 0.00678 0.00223 -0.0055 0.9233 0.6091
-1.500 -0.1552 0.00662 0.00215 -0.0048 0.9088 0.6370
-1.250 -0.1293 0.00648 0.00209 -0.0040 0.8929 0.6642
-1.000 -0.1034 0.00638 0.00203 -0.0032 0.8757 0.6915
-0.750 -0.0777 0.00628 0.00198 -0.0024 0.8571 0.7177
-0.500 -0.0517 0.00622 0.00195 -0.0016 0.8366 0.7435
-0.250 -0.0259 0.00618 0.00193 -0.0008 0.8148 0.7683
0.000 0.0000 0.00618 0.00192 0.0000 0.7923 0.7923
0.250 0.0259 0.00618 0.00193 0.0008 0.7683 0.8148
0.500 0.0517 0.00622 0.00195 0.0016 0.7435 0.8367
0.750 0.0777 0.00628 0.00198 0.0024 0.7178 0.8571
1.000 0.1034 0.00638 0.00203 0.0032 0.6915 0.8757
1.250 0.1293 0.00648 0.00209 0.0040 0.6642 0.8929
1.500 0.1552 0.00662 0.00215 0.0048 0.6371 0.9088
1.750 0.1812 0.00678 0.00223 0.0055 0.6091 0.9233
2.000 0.2089 0.00696 0.00233 0.0059 0.5801 0.9351
2.250 0.2374 0.00716 0.00243 0.0060 0.5509 0.9458
2.500 0.2655 0.00737 0.00254 0.0062 0.5215 0.9566
2.750 0.2995 0.00761 0.00267 0.0050 0.4893 0.9628
3.000 0.3307 0.00786 0.00279 0.0044 0.4576 0.9707
3.250 0.3690 0.00813 0.00293 0.0022 0.4225 0.9740
3.500 0.4066 0.00840 0.00307 0.0001 0.3871 0.9779
3.750 0.4410 0.00869 0.00322 -0.0014 0.3524 0.9832
4.000 0.4798 0.00900 0.00338 -0.0039 0.3152 0.9858
4.250 0.5172 0.00932 0.00354 -0.0061 0.2791 0.9892
4.500 0.5530 0.00966 0.00374 -0.0080 0.2443 0.9931
4.750 0.5904 0.01000 0.00392 -0.0103 0.2096 0.9957
5.000 0.6275 0.01036 0.00414 -0.0125 0.1775 0.9985
5.250 0.6581 0.01072 0.00436 -0.0134 0.1513 1.0000
5.500 0.6796 0.01102 0.00457 -0.0123 0.1312 1.0000
5.750 0.7007 0.01136 0.00482 -0.0112 0.1141 1.0000
6.000 0.7215 0.01170 0.00509 -0.0100 0.1001 1.0000
6.250 0.7424 0.01204 0.00537 -0.0087 0.0889 1.0000
6.500 0.7632 0.01236 0.00568 -0.0074 0.0799 1.0000
6.750 0.7835 0.01275 0.00603 -0.0061 0.0724 1.0000
7.000 0.8036 0.01316 0.00640 -0.0047 0.0657 1.0000
7.250 0.8244 0.01350 0.00676 -0.0034 0.0608 1.0000
7.500 0.8439 0.01399 0.00721 -0.0019 0.0561 1.0000
7.750 0.8646 0.01437 0.00763 -0.0006 0.0526 1.0000
8.000 0.8851 0.01479 0.00804 0.0007 0.0492 1.0000
8.250 0.9040 0.01537 0.00863 0.0023 0.0463 1.0000
8.500 0.9250 0.01577 0.00908 0.0035 0.0439 1.0000
8.750 0.9450 0.01628 0.00958 0.0048 0.0416 1.0000
9.000 0.9632 0.01699 0.01032 0.0064 0.0395 1.0000
9.250 0.9847 0.01743 0.01081 0.0074 0.0377 1.0000
9.500 1.0054 0.01794 0.01135 0.0085 0.0360 1.0000
9.750 1.0224 0.01882 0.01223 0.0100 0.0344 1.0000
10.000 1.0417 0.01951 0.01299 0.0113 0.0333 1.0000
10.250 1.0620 0.02009 0.01364 0.0124 0.0320 1.0000
10.500 1.0817 0.02069 0.01428 0.0134 0.0308 1.0000
10.750 1.0995 0.02144 0.01504 0.0147 0.0297 1.0000
11.000 1.1128 0.02267 0.01631 0.0165 0.0287 1.0000
11.250 1.1309 0.02336 0.01711 0.0177 0.0279 1.0000
11.500 1.1474 0.02416 0.01801 0.0191 0.0271 1.0000
11.750 1.1626 0.02500 0.01893 0.0206 0.0263 1.0000
12.000 1.1753 0.02586 0.01984 0.0224 0.0257 1.0000
12.250 1.1855 0.02684 0.02086 0.0245 0.0251 1.0000
12.500 1.1912 0.02838 0.02244 0.0267 0.0245 1.0000
12.750 1.1984 0.02980 0.02398 0.0286 0.0240 1.0000
13.000 1.2072 0.03098 0.02530 0.0302 0.0235 1.0000
13.250 1.2147 0.03236 0.02681 0.0315 0.0230 1.0000
13.500 1.2208 0.03392 0.02849 0.0326 0.0226 1.0000
13.750 1.2259 0.03568 0.03036 0.0335 0.0222 1.0000
14.000 1.2302 0.03761 0.03239 0.0341 0.0218 1.0000
14.250 1.2337 0.03973 0.03459 0.0343 0.0215 1.0000
14.500 1.2360 0.04209 0.03703 0.0343 0.0212 1.0000
14.750 1.2363 0.04481 0.03983 0.0341 0.0209 1.0000
15.000 1.2327 0.04811 0.04324 0.0336 0.0206 1.0000
15.250 1.2219 0.05247 0.04774 0.0329 0.0203 1.0000
15.500 1.2159 0.05646 0.05191 0.0311 0.0202 1.0000
15.750 1.2073 0.06100 0.05662 0.0289 0.0201 1.0000
16.000 1.1964 0.06607 0.06187 0.0262 0.0200 1.0000
16.250 1.1828 0.07171 0.06768 0.0232 0.0199 1.0000
16.500 1.1669 0.07801 0.07415 0.0196 0.0198 1.0000
16.750 1.1482 0.08501 0.08133 0.0156 0.0198 1.0000
17.000 1.1265 0.09286 0.08936 0.0109 0.0197 1.0000
17.250 1.1011 0.10176 0.09843 0.0056 0.0197 1.0000
17.500 1.0705 0.11207 0.10894 -0.0006 0.0198 1.0000
17.750 1.0302 0.12505 0.12212 -0.0085 0.0199 1.0000
18.000 0.7725 0.21140 0.20887 -0.0516 0.0252 1.0000
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