N-12 (n12-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: N-12 (n12-il) Reynolds number: 500,000 Max Cl/Cd: 55.48 at α=7.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-n12-il-500000-n5.txt Download as CSV file: xf-n12-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: N-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
------ -------- --------- --------- -------- -------- --------
-16.500 -0.9666 0.10310 0.10041 -0.0136 1.0000 0.0096
-16.250 -1.0207 0.08771 0.08481 -0.0223 1.0000 0.0095
-16.000 -1.0562 0.07706 0.07398 -0.0287 1.0000 0.0093
-15.750 -1.0875 0.06765 0.06437 -0.0344 1.0000 0.0092
-15.500 -1.1108 0.05994 0.05647 -0.0391 1.0000 0.0092
-15.250 -1.1269 0.05396 0.05030 -0.0424 1.0000 0.0093
-15.000 -1.1373 0.04937 0.04554 -0.0445 1.0000 0.0094
-14.750 -1.1506 0.04484 0.04081 -0.0459 1.0000 0.0096
-14.500 -1.1586 0.04138 0.03717 -0.0463 1.0000 0.0097
-14.250 -1.1640 0.03850 0.03411 -0.0459 1.0000 0.0099
-14.000 -1.1663 0.03619 0.03166 -0.0450 1.0000 0.0101
-13.750 -1.1682 0.03412 0.02947 -0.0436 1.0000 0.0102
-13.500 -1.1627 0.03286 0.02815 -0.0422 1.0000 0.0106
-13.250 -1.1543 0.03194 0.02718 -0.0408 1.0000 0.0109
-13.000 -1.1443 0.03122 0.02641 -0.0392 1.0000 0.0112
-12.750 -1.1415 0.02988 0.02492 -0.0367 1.0000 0.0114
-12.500 -1.1337 0.02905 0.02401 -0.0345 1.0000 0.0118
-12.250 -1.1267 0.02819 0.02305 -0.0319 1.0000 0.0122
-12.000 -1.1217 0.02720 0.02192 -0.0287 1.0000 0.0127
-11.750 -1.1184 0.02612 0.02070 -0.0252 1.0000 0.0130
-11.500 -1.1114 0.02519 0.01965 -0.0220 1.0000 0.0134
-11.250 -1.0984 0.02461 0.01901 -0.0199 1.0000 0.0137
-11.000 -1.0814 0.02440 0.01879 -0.0182 1.0000 0.0142
-10.750 -1.0644 0.02417 0.01852 -0.0166 1.0000 0.0146
-10.500 -1.0488 0.02368 0.01796 -0.0147 1.0000 0.0151
-10.250 -1.0319 0.02330 0.01751 -0.0130 1.0000 0.0158
-10.000 -1.0166 0.02260 0.01669 -0.0111 1.0000 0.0165
-9.750 -1.0006 0.02189 0.01586 -0.0091 1.0000 0.0172
-9.500 -0.9838 0.02127 0.01512 -0.0073 1.0000 0.0177
-9.250 -0.9680 0.02059 0.01440 -0.0054 1.0000 0.0182
-9.000 -0.9496 0.02022 0.01400 -0.0039 1.0000 0.0186
-8.750 -0.9305 0.01995 0.01370 -0.0025 1.0000 0.0193
-8.500 -0.9118 0.01955 0.01326 -0.0009 1.0000 0.0199
-8.250 -0.8934 0.01906 0.01270 0.0007 1.0000 0.0207
-8.000 -0.8747 0.01856 0.01213 0.0023 1.0000 0.0214
-7.750 -0.8550 0.01823 0.01173 0.0038 1.0000 0.0223
-7.500 -0.8356 0.01783 0.01126 0.0054 1.0000 0.0228
-7.250 -0.8160 0.01748 0.01084 0.0069 1.0000 0.0232
-7.000 -0.8001 0.01660 0.00992 0.0090 1.0000 0.0238
-6.750 -0.7840 0.01587 0.00918 0.0110 1.0000 0.0246
-6.500 -0.7626 0.01540 0.00869 0.0121 0.9996 0.0254
-6.250 -0.7304 0.01489 0.00814 0.0108 0.9974 0.0261
-6.000 -0.6964 0.01442 0.00764 0.0092 0.9946 0.0269
-5.750 -0.6640 0.01394 0.00713 0.0079 0.9912 0.0278
-5.500 -0.6317 0.01349 0.00664 0.0067 0.9876 0.0285
-5.250 -0.5992 0.01304 0.00616 0.0055 0.9846 0.0290
-5.000 -0.5716 0.01263 0.00572 0.0054 0.9789 0.0294
-4.500 -0.5143 0.01194 0.00497 0.0049 0.9669 0.0304
-4.250 -0.4866 0.01161 0.00463 0.0048 0.9596 0.0308
-4.000 -0.4589 0.01117 0.00414 0.0048 0.9507 0.0318
-3.750 -0.4291 0.01082 0.00376 0.0044 0.9415 0.0327
-3.500 -0.3923 0.01050 0.00341 0.0024 0.9333 0.0336
-3.250 -0.3513 0.01020 0.00309 -0.0005 0.9252 0.0347
-3.000 -0.3027 0.00993 0.00279 -0.0051 0.9169 0.0361
-2.750 -0.2516 0.00968 0.00250 -0.0103 0.9039 0.0380
-2.500 -0.2080 0.00951 0.00226 -0.0138 0.8818 0.0414
-2.250 -0.1787 0.00916 0.00204 -0.0143 0.8570 0.0981
-2.000 -0.1525 0.00905 0.00192 -0.0139 0.8325 0.1160
-1.750 -0.1283 0.00893 0.00181 -0.0130 0.8075 0.1344
-1.500 -0.1071 0.00868 0.00166 -0.0116 0.7778 0.1855
-1.250 -0.0928 0.00807 0.00149 -0.0090 0.7400 0.3351
-1.000 -0.0717 0.00799 0.00142 -0.0075 0.7053 0.3769
-0.750 -0.0501 0.00794 0.00136 -0.0061 0.6736 0.4071
-0.500 -0.0286 0.00790 0.00131 -0.0047 0.6420 0.4353
-0.250 -0.0080 0.00780 0.00126 -0.0032 0.6129 0.4760
0.000 0.0067 0.00742 0.00123 -0.0004 0.5869 0.5877
0.250 0.0236 0.00722 0.00125 0.0020 0.5600 0.6699
0.500 0.0421 0.00711 0.00129 0.0042 0.5327 0.7302
0.750 0.0625 0.00713 0.00135 0.0060 0.4976 0.7728
1.000 0.0835 0.00732 0.00142 0.0075 0.4410 0.7994
1.250 0.1040 0.00765 0.00150 0.0091 0.3629 0.8194
1.500 0.1274 0.00787 0.00159 0.0100 0.3220 0.8359
1.750 0.1524 0.00801 0.00168 0.0107 0.2971 0.8534
2.000 0.1785 0.00814 0.00178 0.0111 0.2771 0.8718
2.250 0.2069 0.00826 0.00188 0.0110 0.2596 0.8873
2.500 0.2393 0.00842 0.00200 0.0100 0.2393 0.9013
2.750 0.2776 0.00859 0.00216 0.0077 0.2238 0.9135
3.000 0.3187 0.00885 0.00235 0.0046 0.2006 0.9239
3.250 0.3525 0.00943 0.00260 0.0030 0.1189 0.9302
3.500 0.3879 0.00972 0.00284 0.0012 0.1045 0.9357
3.750 0.4246 0.00998 0.00308 -0.0008 0.0928 0.9402
4.000 0.4555 0.01037 0.00331 -0.0017 0.0554 0.9463
4.250 0.4860 0.01071 0.00359 -0.0023 0.0440 0.9515
4.500 0.5162 0.01098 0.00386 -0.0029 0.0411 0.9569
4.750 0.5435 0.01126 0.00416 -0.0028 0.0391 0.9637
5.000 0.5737 0.01159 0.00450 -0.0034 0.0364 0.9684
5.500 0.6320 0.01226 0.00525 -0.0042 0.0340 0.9783
5.750 0.6614 0.01260 0.00563 -0.0046 0.0332 0.9834
6.000 0.6928 0.01295 0.00603 -0.0056 0.0321 0.9866
6.250 0.7243 0.01332 0.00643 -0.0066 0.0307 0.9896
6.500 0.7540 0.01371 0.00686 -0.0073 0.0296 0.9926
6.750 0.7834 0.01416 0.00734 -0.0079 0.0283 0.9951
7.000 0.8122 0.01484 0.00805 -0.0086 0.0267 0.9976
7.250 0.8427 0.01529 0.00856 -0.0095 0.0258 0.9996
7.500 0.8649 0.01559 0.00893 -0.0085 0.0250 1.0000
7.750 0.8830 0.01594 0.00932 -0.0068 0.0240 1.0000
8.000 0.9012 0.01630 0.00973 -0.0050 0.0230 1.0000
8.250 0.9194 0.01667 0.01014 -0.0033 0.0220 1.0000
8.500 0.9384 0.01698 0.01047 -0.0017 0.0210 1.0000
8.750 0.9550 0.01749 0.01100 0.0002 0.0200 1.0000
9.000 0.9719 0.01799 0.01156 0.0021 0.0193 1.0000
9.250 0.9895 0.01843 0.01208 0.0039 0.0186 1.0000
9.500 1.0077 0.01881 0.01253 0.0056 0.0175 1.0000
9.750 1.0253 0.01924 0.01301 0.0073 0.0167 1.0000
10.000 1.0441 0.01954 0.01333 0.0088 0.0158 1.0000
10.250 1.0606 0.02003 0.01385 0.0106 0.0151 1.0000
10.500 1.0748 0.02067 0.01456 0.0128 0.0144 1.0000
10.750 1.0891 0.02130 0.01528 0.0150 0.0138 1.0000
11.000 1.1027 0.02195 0.01602 0.0172 0.0133 1.0000
11.250 1.1168 0.02253 0.01667 0.0193 0.0127 1.0000
11.500 1.1292 0.02321 0.01742 0.0216 0.0122 1.0000
11.750 1.1402 0.02380 0.01807 0.0242 0.0118 1.0000
12.000 1.1472 0.02450 0.01883 0.0274 0.0114 1.0000
12.250 1.1501 0.02550 0.01990 0.0309 0.0109 1.0000
12.500 1.1565 0.02642 0.02095 0.0337 0.0106 1.0000
12.750 1.1633 0.02738 0.02202 0.0362 0.0103 1.0000
13.000 1.1684 0.02851 0.02327 0.0386 0.0099 1.0000
13.250 1.1717 0.02985 0.02473 0.0409 0.0098 1.0000
13.500 1.1750 0.03129 0.02630 0.0427 0.0095 1.0000
13.750 1.1775 0.03291 0.02802 0.0442 0.0092 1.0000
14.000 1.1783 0.03481 0.03005 0.0454 0.0091 1.0000
14.250 1.1783 0.03694 0.03230 0.0461 0.0089 1.0000
14.500 1.1772 0.03938 0.03486 0.0463 0.0087 1.0000
14.750 1.1726 0.04245 0.03808 0.0460 0.0086 1.0000
15.000 1.1670 0.04596 0.04170 0.0449 0.0084 1.0000
15.250 1.1565 0.05046 0.04636 0.0430 0.0083 1.0000
15.500 1.1453 0.05540 0.05145 0.0405 0.0083 1.0000
15.750 1.1290 0.06152 0.05772 0.0371 0.0081 1.0000
16.000 1.1096 0.06846 0.06482 0.0331 0.0081 1.0000
16.250 1.0936 0.07506 0.07159 0.0294 0.0083 1.0000
16.500 1.0664 0.08378 0.08046 0.0245 0.0082 1.0000
16.750 1.0403 0.09247 0.08930 0.0198 0.0083 1.0000
17.000 1.0103 0.10212 0.09910 0.0147 0.0084 1.0000
17.250 0.9626 0.11596 0.11316 0.0074 0.0086 1.0000
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Polar data table (+)
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