N-12 (n12-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: N-12 (n12-il) Reynolds number: 200,000 Max Cl/Cd: 42.87 at α=5.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-n12-il-200000-n5.txt Download as CSV file: xf-n12-il-200000-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 = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-13.000 -0.6929 0.10942 0.10555 -0.0113 1.0000 0.0204
-12.750 -0.8410 0.06856 0.06426 -0.0388 1.0000 0.0184
-12.500 -0.8677 0.06168 0.05715 -0.0429 1.0000 0.0183
-12.250 -0.8866 0.05697 0.05226 -0.0445 1.0000 0.0183
-12.000 -0.9012 0.05341 0.04853 -0.0445 1.0000 0.0185
-11.750 -0.9154 0.05028 0.04523 -0.0433 1.0000 0.0186
-11.500 -0.9250 0.04796 0.04274 -0.0412 1.0000 0.0188
-11.250 -0.9332 0.04594 0.04058 -0.0384 1.0000 0.0191
-11.000 -0.9413 0.04412 0.03860 -0.0346 1.0000 0.0195
-10.750 -0.9467 0.04225 0.03655 -0.0309 1.0000 0.0198
-10.500 -0.9471 0.04042 0.03450 -0.0277 1.0000 0.0204
-10.250 -0.9459 0.03862 0.03244 -0.0245 1.0000 0.0213
-10.000 -0.9433 0.03680 0.03027 -0.0213 1.0000 0.0222
-9.750 -0.9381 0.03537 0.02847 -0.0181 1.0000 0.0230
-9.500 -0.9302 0.03333 0.02614 -0.0155 1.0000 0.0236
-9.250 -0.9168 0.03157 0.02432 -0.0138 1.0000 0.0244
-9.000 -0.9026 0.03029 0.02293 -0.0120 1.0000 0.0251
-8.750 -0.8876 0.02921 0.02175 -0.0102 1.0000 0.0262
-8.500 -0.8718 0.02813 0.02052 -0.0083 1.0000 0.0273
-8.250 -0.8552 0.02698 0.01919 -0.0065 1.0000 0.0283
-8.000 -0.8376 0.02592 0.01795 -0.0048 1.0000 0.0292
-7.750 -0.8197 0.02522 0.01705 -0.0031 1.0000 0.0302
-7.500 -0.8014 0.02391 0.01562 -0.0015 1.0000 0.0313
-7.250 -0.7829 0.02249 0.01419 -0.0001 1.0000 0.0323
-7.000 -0.7646 0.02149 0.01317 0.0014 1.0000 0.0331
-6.750 -0.7467 0.02065 0.01231 0.0031 1.0000 0.0342
-6.500 -0.7287 0.01991 0.01152 0.0048 1.0000 0.0354
-6.250 -0.7109 0.01922 0.01078 0.0066 1.0000 0.0365
-6.000 -0.6932 0.01857 0.01009 0.0085 1.0000 0.0372
-5.750 -0.6759 0.01796 0.00943 0.0104 1.0000 0.0379
-5.500 -0.6587 0.01741 0.00884 0.0124 1.0000 0.0385
-5.250 -0.6413 0.01694 0.00831 0.0143 1.0000 0.0392
-5.000 -0.6237 0.01655 0.00787 0.0162 1.0000 0.0400
-4.750 -0.6079 0.01603 0.00731 0.0184 1.0000 0.0410
-4.500 -0.5838 0.01554 0.00676 0.0189 0.9983 0.0421
-4.250 -0.5493 0.01512 0.00627 0.0172 0.9940 0.0434
-4.000 -0.5162 0.01472 0.00582 0.0159 0.9890 0.0450
-3.750 -0.4817 0.01439 0.00545 0.0143 0.9847 0.0469
-3.500 -0.4506 0.01408 0.00508 0.0134 0.9783 0.0491
-3.250 -0.4181 0.01374 0.00475 0.0123 0.9728 0.0554
-3.000 -0.3897 0.01317 0.00448 0.0118 0.9655 0.1092
-2.750 -0.3597 0.01283 0.00424 0.0112 0.9584 0.1346
-2.500 -0.3288 0.01242 0.00399 0.0104 0.9516 0.1688
-2.250 -0.3024 0.01175 0.00371 0.0103 0.9428 0.2503
-2.000 -0.2707 0.01111 0.00351 0.0093 0.9351 0.3566
-1.750 -0.2377 0.01068 0.00329 0.0082 0.9239 0.4144
-1.500 -0.2014 0.01015 0.00305 0.0064 0.9119 0.4757
-1.250 -0.1685 0.00950 0.00292 0.0054 0.8999 0.5874
-1.000 -0.1342 0.00905 0.00292 0.0045 0.8874 0.6978
-0.750 -0.0950 0.00885 0.00302 0.0027 0.8734 0.7770
-0.500 -0.0563 0.00882 0.00304 0.0009 0.8550 0.8130
-0.250 -0.0192 0.00883 0.00302 -0.0007 0.8332 0.8342
0.000 0.0155 0.00887 0.00302 -0.0018 0.8079 0.8535
0.250 0.0498 0.00894 0.00301 -0.0027 0.7769 0.8704
0.500 0.0855 0.00905 0.00304 -0.0040 0.7439 0.8853
0.750 0.1223 0.00920 0.00308 -0.0055 0.7106 0.8967
1.000 0.1542 0.00936 0.00311 -0.0061 0.6744 0.9062
1.250 0.1903 0.00957 0.00318 -0.0076 0.6375 0.9127
1.500 0.2222 0.00979 0.00326 -0.0083 0.6024 0.9212
1.750 0.2580 0.01006 0.00339 -0.0098 0.5606 0.9271
2.000 0.2856 0.01039 0.00349 -0.0097 0.5078 0.9355
2.250 0.3170 0.01082 0.00364 -0.0104 0.4378 0.9406
2.500 0.3413 0.01131 0.00379 -0.0098 0.3680 0.9492
3.000 0.4022 0.01200 0.00420 -0.0112 0.3004 0.9615
3.250 0.4360 0.01226 0.00441 -0.0126 0.2803 0.9663
3.500 0.4659 0.01255 0.00462 -0.0132 0.2563 0.9728
3.750 0.4991 0.01284 0.00484 -0.0145 0.2283 0.9777
4.000 0.5274 0.01351 0.00507 -0.0152 0.1327 0.9842
4.250 0.5601 0.01411 0.00550 -0.0166 0.1038 0.9887
4.500 0.5925 0.01449 0.00588 -0.0179 0.0786 0.9933
4.750 0.6246 0.01492 0.00620 -0.0191 0.0598 0.9971
5.000 0.6549 0.01534 0.00661 -0.0199 0.0535 1.0000
5.250 0.6722 0.01568 0.00702 -0.0180 0.0506 1.0000
5.500 0.6888 0.01607 0.00744 -0.0159 0.0479 1.0000
5.750 0.7042 0.01660 0.00799 -0.0137 0.0453 1.0000
6.000 0.7202 0.01708 0.00853 -0.0115 0.0439 1.0000
6.250 0.7364 0.01758 0.00912 -0.0094 0.0427 1.0000
6.500 0.7527 0.01811 0.00972 -0.0073 0.0414 1.0000
6.750 0.7691 0.01867 0.01034 -0.0052 0.0397 1.0000
7.000 0.7852 0.01929 0.01100 -0.0031 0.0380 1.0000
7.250 0.8006 0.02003 0.01177 -0.0010 0.0366 1.0000
7.500 0.8141 0.02109 0.01285 0.0014 0.0350 1.0000
7.750 0.8305 0.02190 0.01376 0.0034 0.0338 1.0000
8.000 0.8476 0.02260 0.01458 0.0052 0.0325 1.0000
8.250 0.8642 0.02345 0.01554 0.0071 0.0311 1.0000
8.500 0.8804 0.02430 0.01648 0.0090 0.0296 1.0000
8.750 0.8959 0.02513 0.01736 0.0109 0.0282 1.0000
9.000 0.9105 0.02620 0.01847 0.0128 0.0270 1.0000
9.250 0.9242 0.02780 0.02019 0.0147 0.0259 1.0000
9.500 0.9385 0.02881 0.02142 0.0169 0.0249 1.0000
9.750 0.9516 0.02994 0.02276 0.0190 0.0238 1.0000
10.000 0.9632 0.03098 0.02398 0.0213 0.0225 1.0000
10.250 0.9740 0.03204 0.02517 0.0236 0.0216 1.0000
10.500 0.9836 0.03317 0.02640 0.0259 0.0209 1.0000
10.750 0.9916 0.03438 0.02769 0.0283 0.0203 1.0000
11.000 0.9962 0.03610 0.02952 0.0309 0.0197 1.0000
11.250 0.9938 0.03780 0.03148 0.0347 0.0193 1.0000
11.500 0.9879 0.03980 0.03376 0.0386 0.0189 1.0000
11.750 0.9802 0.04193 0.03618 0.0419 0.0183 1.0000
12.000 0.9702 0.04454 0.03904 0.0444 0.0180 1.0000
12.250 0.9572 0.04760 0.04235 0.0461 0.0177 1.0000
12.500 0.9477 0.05042 0.04536 0.0467 0.0170 1.0000
12.750 0.9281 0.05508 0.05027 0.0460 0.0171 1.0000
13.000 0.9141 0.05948 0.05485 0.0442 0.0167 1.0000
13.250 0.8828 0.06748 0.06311 0.0395 0.0172 1.0000
13.500 0.8489 0.07736 0.07322 0.0326 0.0174 1.0000
13.750 0.8041 0.09126 0.08729 0.0231 0.0182 1.0000
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