NACA 0012 AIRFOILS (n0012-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA 0012 AIRFOILS (n0012-il) Reynolds number: 200,000 Max Cl/Cd: 45.9 at α=6.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-n0012-il-200000-n5.txt Download as CSV file: xf-n0012-il-200000-n5.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 = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-16.250 -0.9667 0.11253 0.10820 0.0005 1.0000 0.0231
-16.000 -1.0096 0.09915 0.09458 -0.0077 1.0000 0.0230
-15.750 -1.0389 0.08931 0.08453 -0.0137 1.0000 0.0229
-15.500 -1.0622 0.08119 0.07620 -0.0186 1.0000 0.0230
-15.250 -1.0812 0.07419 0.06899 -0.0227 1.0000 0.0231
-15.000 -1.0967 0.06806 0.06266 -0.0262 1.0000 0.0233
-14.750 -1.1094 0.06262 0.05700 -0.0290 1.0000 0.0235
-14.500 -1.1197 0.05782 0.05198 -0.0313 1.0000 0.0237
-14.250 -1.1276 0.05355 0.04747 -0.0330 1.0000 0.0241
-14.000 -1.1323 0.04997 0.04371 -0.0340 1.0000 0.0244
-13.750 -1.1327 0.04715 0.04081 -0.0345 1.0000 0.0248
-13.500 -1.1319 0.04462 0.03820 -0.0347 1.0000 0.0252
-13.250 -1.1301 0.04232 0.03579 -0.0345 1.0000 0.0256
-13.000 -1.1275 0.04022 0.03357 -0.0340 1.0000 0.0261
-12.750 -1.1240 0.03828 0.03149 -0.0331 1.0000 0.0267
-12.500 -1.1194 0.03648 0.02954 -0.0319 1.0000 0.0274
-12.250 -1.1137 0.03481 0.02770 -0.0305 1.0000 0.0280
-12.000 -1.1066 0.03329 0.02599 -0.0288 1.0000 0.0287
-11.750 -1.0996 0.03187 0.02450 -0.0270 1.0000 0.0293
-11.500 -1.0912 0.03072 0.02330 -0.0250 1.0000 0.0300
-11.250 -1.0809 0.02971 0.02221 -0.0231 1.0000 0.0309
-11.000 -1.0677 0.02869 0.02109 -0.0215 1.0000 0.0321
-10.750 -1.0533 0.02767 0.01994 -0.0200 1.0000 0.0333
-10.500 -1.0386 0.02662 0.01878 -0.0185 1.0000 0.0344
-10.250 -1.0236 0.02565 0.01778 -0.0170 1.0000 0.0356
-10.000 -1.0068 0.02481 0.01689 -0.0157 1.0000 0.0370
-9.750 -0.9889 0.02402 0.01600 -0.0144 1.0000 0.0387
-9.500 -0.9710 0.02320 0.01509 -0.0131 1.0000 0.0405
-9.250 -0.9534 0.02240 0.01427 -0.0118 1.0000 0.0424
-9.000 -0.9344 0.02170 0.01352 -0.0106 1.0000 0.0445
-8.750 -0.9146 0.02106 0.01278 -0.0094 1.0000 0.0470
-8.500 -0.8963 0.02031 0.01204 -0.0080 1.0000 0.0496
-8.250 -0.8764 0.01972 0.01140 -0.0068 1.0000 0.0528
-8.000 -0.8566 0.01913 0.01076 -0.0056 1.0000 0.0560
-7.750 -0.8372 0.01853 0.01017 -0.0043 1.0000 0.0600
-7.500 -0.8167 0.01805 0.00961 -0.0030 1.0000 0.0645
-7.250 -0.7974 0.01747 0.00908 -0.0016 1.0000 0.0696
-7.000 -0.7770 0.01701 0.00859 -0.0004 1.0000 0.0756
-6.750 -0.7570 0.01651 0.00812 0.0009 1.0000 0.0829
-6.500 -0.7367 0.01605 0.00768 0.0022 1.0000 0.0911
-6.250 -0.7162 0.01563 0.00727 0.0035 1.0000 0.1010
-6.000 -0.6956 0.01522 0.00690 0.0047 1.0000 0.1128
-5.750 -0.6751 0.01481 0.00654 0.0060 1.0000 0.1269
-5.500 -0.6546 0.01441 0.00621 0.0072 1.0000 0.1430
-5.250 -0.6340 0.01402 0.00592 0.0084 1.0000 0.1619
-5.000 -0.6131 0.01367 0.00564 0.0095 1.0000 0.1832
-4.750 -0.5922 0.01332 0.00540 0.0106 1.0000 0.2067
-4.500 -0.5624 0.01296 0.00516 0.0099 0.9973 0.2360
-4.250 -0.5268 0.01259 0.00493 0.0079 0.9928 0.2698
-4.000 -0.4921 0.01224 0.00471 0.0062 0.9872 0.3045
-3.750 -0.4556 0.01192 0.00453 0.0041 0.9826 0.3407
-3.500 -0.4223 0.01161 0.00435 0.0029 0.9756 0.3754
-3.250 -0.3855 0.01132 0.00420 0.0009 0.9705 0.4111
-3.000 -0.3536 0.01104 0.00405 0.0000 0.9620 0.4444
-2.750 -0.3182 0.01078 0.00392 -0.0016 0.9556 0.4785
-2.500 -0.2881 0.01055 0.00381 -0.0020 0.9449 0.5102
-2.250 -0.2563 0.01033 0.00370 -0.0026 0.9351 0.5417
-2.000 -0.2240 0.01011 0.00360 -0.0033 0.9249 0.5724
-1.750 -0.1949 0.00991 0.00351 -0.0033 0.9118 0.6016
-1.500 -0.1655 0.00974 0.00343 -0.0033 0.8980 0.6303
-1.000 -0.1083 0.00944 0.00330 -0.0027 0.8666 0.6854
-0.750 -0.0807 0.00933 0.00325 -0.0022 0.8485 0.7118
-0.500 -0.0535 0.00925 0.00321 -0.0016 0.8289 0.7374
-0.250 -0.0265 0.00919 0.00318 -0.0008 0.8083 0.7618
0.000 0.0000 0.00918 0.00318 0.0000 0.7855 0.7854
0.250 0.0265 0.00919 0.00318 0.0008 0.7618 0.8082
0.500 0.0535 0.00925 0.00321 0.0016 0.7374 0.8289
0.750 0.0807 0.00933 0.00325 0.0022 0.7117 0.8485
1.000 0.1083 0.00944 0.00330 0.0028 0.6855 0.8667
1.500 0.1655 0.00974 0.00343 0.0033 0.6303 0.8981
1.750 0.1949 0.00991 0.00351 0.0033 0.6017 0.9118
2.000 0.2240 0.01011 0.00359 0.0033 0.5725 0.9249
2.250 0.2563 0.01033 0.00370 0.0026 0.5417 0.9351
2.500 0.2881 0.01055 0.00381 0.0020 0.5101 0.9449
2.750 0.3181 0.01078 0.00392 0.0016 0.4785 0.9556
3.000 0.3536 0.01104 0.00405 0.0000 0.4444 0.9620
3.250 0.3855 0.01132 0.00420 -0.0009 0.4111 0.9705
3.500 0.4223 0.01161 0.00435 -0.0029 0.3754 0.9756
3.750 0.4556 0.01192 0.00453 -0.0041 0.3407 0.9826
4.000 0.4922 0.01223 0.00471 -0.0062 0.3045 0.9872
4.250 0.5268 0.01259 0.00492 -0.0079 0.2698 0.9928
4.500 0.5624 0.01296 0.00516 -0.0099 0.2359 0.9973
4.750 0.5921 0.01332 0.00540 -0.0106 0.2067 1.0000
5.000 0.6130 0.01367 0.00564 -0.0095 0.1832 1.0000
5.250 0.6339 0.01402 0.00591 -0.0083 0.1620 1.0000
5.500 0.6546 0.01441 0.00621 -0.0072 0.1430 1.0000
5.750 0.6751 0.01481 0.00653 -0.0059 0.1269 1.0000
6.000 0.6956 0.01522 0.00689 -0.0047 0.1128 1.0000
6.250 0.7162 0.01563 0.00727 -0.0035 0.1010 1.0000
6.500 0.7367 0.01605 0.00767 -0.0022 0.0911 1.0000
6.750 0.7570 0.01651 0.00811 -0.0009 0.0829 1.0000
7.000 0.7769 0.01701 0.00859 0.0004 0.0756 1.0000
7.250 0.7974 0.01747 0.00908 0.0017 0.0696 1.0000
7.500 0.8167 0.01805 0.00961 0.0030 0.0645 1.0000
7.750 0.8372 0.01853 0.01017 0.0043 0.0600 1.0000
8.000 0.8567 0.01913 0.01076 0.0056 0.0560 1.0000
8.250 0.8765 0.01972 0.01140 0.0068 0.0528 1.0000
8.500 0.8964 0.02031 0.01204 0.0080 0.0496 1.0000
8.750 0.9147 0.02106 0.01277 0.0094 0.0470 1.0000
9.000 0.9345 0.02170 0.01352 0.0106 0.0445 1.0000
9.250 0.9535 0.02239 0.01427 0.0118 0.0424 1.0000
9.500 0.9711 0.02320 0.01509 0.0131 0.0405 1.0000
9.750 0.9891 0.02401 0.01600 0.0144 0.0387 1.0000
10.000 1.0069 0.02481 0.01688 0.0157 0.0370 1.0000
10.250 1.0238 0.02565 0.01778 0.0170 0.0355 1.0000
10.500 1.0388 0.02662 0.01878 0.0184 0.0344 1.0000
10.750 1.0535 0.02767 0.01994 0.0200 0.0333 1.0000
11.000 1.0680 0.02869 0.02109 0.0215 0.0321 1.0000
11.250 1.0812 0.02971 0.02222 0.0230 0.0309 1.0000
11.500 1.0916 0.03073 0.02330 0.0249 0.0300 1.0000
11.750 1.1001 0.03188 0.02450 0.0269 0.0293 1.0000
12.000 1.1072 0.03329 0.02599 0.0287 0.0287 1.0000
12.250 1.1144 0.03481 0.02770 0.0304 0.0280 1.0000
12.500 1.1201 0.03648 0.02954 0.0318 0.0273 1.0000
12.750 1.1248 0.03828 0.03149 0.0330 0.0267 1.0000
13.000 1.1284 0.04022 0.03357 0.0339 0.0261 1.0000
13.250 1.1311 0.04231 0.03578 0.0344 0.0256 1.0000
13.500 1.1330 0.04460 0.03817 0.0345 0.0251 1.0000
13.750 1.1340 0.04712 0.04077 0.0343 0.0247 1.0000
14.000 1.1336 0.04995 0.04369 0.0339 0.0244 1.0000
14.250 1.1288 0.05355 0.04748 0.0328 0.0240 1.0000
14.500 1.1209 0.05783 0.05199 0.0311 0.0237 1.0000
14.750 1.1107 0.06264 0.05702 0.0288 0.0235 1.0000
15.000 1.0981 0.06808 0.06268 0.0259 0.0232 1.0000
15.250 1.0824 0.07424 0.06904 0.0225 0.0231 1.0000
15.500 1.0636 0.08123 0.07625 0.0183 0.0230 1.0000
15.750 1.0402 0.08939 0.08461 0.0134 0.0229 1.0000
16.000 1.0107 0.09929 0.09473 0.0073 0.0230 1.0000
16.250 0.9672 0.11285 0.10853 -0.0010 0.0231 1.0000
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