N-13 (n13-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: N-13 (n13-il) Reynolds number: 200,000 Max Cl/Cd: 49.38 at α=4° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-n13-il-200000.txt Download as CSV file: xf-n13-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: N-13
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-14.250 -0.7135 0.11388 0.11001 -0.0219 1.0000 0.0333
-14.000 -0.7454 0.10172 0.09784 -0.0281 1.0000 0.0325
-13.750 -0.7881 0.08812 0.08414 -0.0368 1.0000 0.0313
-13.500 -0.8312 0.07659 0.07242 -0.0447 1.0000 0.0306
-13.250 -0.8707 0.06768 0.06328 -0.0499 1.0000 0.0296
-13.000 -0.9048 0.06094 0.05626 -0.0523 1.0000 0.0292
-12.750 -0.9235 0.05682 0.05196 -0.0526 1.0000 0.0295
-12.500 -0.9476 0.05254 0.04741 -0.0516 1.0000 0.0293
-12.250 -0.9652 0.04926 0.04389 -0.0494 1.0000 0.0293
-12.000 -0.9802 0.04638 0.04076 -0.0463 1.0000 0.0293
-11.750 -0.9897 0.04414 0.03832 -0.0428 1.0000 0.0297
-11.500 -0.9987 0.04198 0.03595 -0.0387 1.0000 0.0300
-11.250 -1.0038 0.04038 0.03415 -0.0345 1.0000 0.0306
-11.000 -1.0062 0.03886 0.03241 -0.0304 1.0000 0.0317
-10.750 -1.0056 0.03707 0.03033 -0.0267 1.0000 0.0324
-10.500 -1.0027 0.03557 0.02853 -0.0231 1.0000 0.0331
-10.250 -0.9949 0.03291 0.02563 -0.0206 1.0000 0.0342
-10.000 -0.9810 0.03109 0.02378 -0.0189 1.0000 0.0355
-9.750 -0.9681 0.02979 0.02240 -0.0167 1.0000 0.0369
-9.500 -0.9551 0.02863 0.02110 -0.0143 1.0000 0.0388
-9.250 -0.9424 0.02774 0.01999 -0.0117 1.0000 0.0409
-9.000 -0.9271 0.02573 0.01794 -0.0100 1.0000 0.0438
-8.750 -0.9134 0.02457 0.01679 -0.0078 1.0000 0.0468
-8.500 -0.8997 0.02360 0.01568 -0.0053 1.0000 0.0507
-8.250 -0.8899 0.02192 0.01404 -0.0024 1.0000 0.0559
-8.000 -0.8783 0.02106 0.01310 0.0004 1.0000 0.0617
-7.750 -0.8694 0.02006 0.01217 0.0037 1.0000 0.0680
-7.500 -0.8563 0.01951 0.01156 0.0064 1.0000 0.0742
-7.250 -0.8428 0.01912 0.01122 0.0089 1.0000 0.0808
-7.000 -0.8283 0.01874 0.01079 0.0113 1.0000 0.0876
-6.750 -0.8127 0.01847 0.01048 0.0135 1.0000 0.0951
-6.500 -0.7985 0.01798 0.00999 0.0159 1.0000 0.1033
-6.250 -0.7830 0.01758 0.00953 0.0182 1.0000 0.1139
-6.000 -0.7697 0.01693 0.00891 0.0207 1.0000 0.1277
-5.750 -0.7569 0.01622 0.00831 0.0233 1.0000 0.1434
-5.500 -0.7419 0.01572 0.00787 0.0256 1.0000 0.1593
-5.250 -0.7253 0.01533 0.00753 0.0276 1.0000 0.1747
-5.000 -0.7084 0.01497 0.00721 0.0295 1.0000 0.1909
-4.750 -0.6916 0.01460 0.00689 0.0314 1.0000 0.2088
-4.500 -0.6756 0.01416 0.00657 0.0334 1.0000 0.2333
-4.250 -0.6611 0.01363 0.00626 0.0356 1.0000 0.2738
-4.000 -0.6486 0.01303 0.00606 0.0382 1.0000 0.3487
-3.750 -0.6346 0.01263 0.00591 0.0406 1.0000 0.4144
-3.500 -0.6208 0.01229 0.00583 0.0431 1.0000 0.4693
-3.250 -0.5950 0.01212 0.00590 0.0432 0.9970 0.5282
-3.000 -0.5590 0.01210 0.00607 0.0413 0.9911 0.5838
-2.750 -0.5221 0.01214 0.00624 0.0393 0.9851 0.6293
-2.500 -0.4880 0.01210 0.00629 0.0380 0.9784 0.6650
-2.250 -0.4500 0.01211 0.00641 0.0359 0.9730 0.7030
-2.000 -0.4174 0.01200 0.00641 0.0350 0.9654 0.7374
-1.750 -0.3768 0.01197 0.00649 0.0326 0.9607 0.7683
-1.500 -0.3398 0.01188 0.00651 0.0310 0.9529 0.7976
-1.250 -0.2908 0.01184 0.00653 0.0269 0.9480 0.8229
-1.000 -0.2465 0.01183 0.00658 0.0240 0.9406 0.8489
-0.750 -0.1925 0.01192 0.00670 0.0192 0.9362 0.8702
-0.500 -0.1375 0.01202 0.00681 0.0141 0.9335 0.8866
-0.250 -0.0918 0.01214 0.00694 0.0109 0.9271 0.9001
0.000 -0.0434 0.01213 0.00693 0.0070 0.9225 0.9106
0.250 0.0162 0.01212 0.00692 0.0009 0.9202 0.9146
0.500 0.0800 0.01212 0.00694 -0.0060 0.9181 0.9197
0.750 0.1313 0.01212 0.00696 -0.0103 0.9085 0.9265
1.000 0.1954 0.01200 0.00686 -0.0171 0.8994 0.9282
1.250 0.2526 0.01194 0.00681 -0.0227 0.8864 0.9312
1.500 0.2877 0.01195 0.00683 -0.0239 0.8676 0.9402
1.750 0.3343 0.01191 0.00683 -0.0274 0.8475 0.9434
2.000 0.3736 0.01187 0.00681 -0.0294 0.8211 0.9499
2.250 0.4124 0.01178 0.00667 -0.0311 0.7835 0.9574
2.500 0.4582 0.01178 0.00647 -0.0341 0.7328 0.9625
2.750 0.4942 0.01199 0.00646 -0.0355 0.6868 0.9706
3.000 0.5329 0.01210 0.00641 -0.0376 0.6347 0.9764
3.250 0.5651 0.01224 0.00637 -0.0386 0.5716 0.9841
3.500 0.5984 0.01248 0.00621 -0.0399 0.4792 0.9912
3.750 0.6316 0.01286 0.00619 -0.0414 0.4018 0.9978
4.000 0.6523 0.01321 0.00629 -0.0406 0.3479 1.0000
4.250 0.6645 0.01356 0.00644 -0.0379 0.2998 1.0000
4.500 0.6768 0.01398 0.00664 -0.0352 0.2531 1.0000
4.750 0.6889 0.01449 0.00692 -0.0325 0.2110 1.0000
5.000 0.7016 0.01505 0.00728 -0.0299 0.1737 1.0000
5.250 0.7146 0.01563 0.00770 -0.0272 0.1480 1.0000
5.500 0.7285 0.01617 0.00816 -0.0247 0.1301 1.0000
5.750 0.7428 0.01672 0.00865 -0.0222 0.1176 1.0000
6.000 0.7565 0.01736 0.00921 -0.0197 0.1081 1.0000
6.250 0.7724 0.01783 0.00973 -0.0175 0.1003 1.0000
6.500 0.7864 0.01859 0.01044 -0.0150 0.0937 1.0000
6.750 0.8025 0.01907 0.01097 -0.0128 0.0871 1.0000
7.000 0.8168 0.02003 0.01186 -0.0105 0.0816 1.0000
7.250 0.8331 0.02051 0.01247 -0.0083 0.0765 1.0000
7.500 0.8481 0.02124 0.01316 -0.0061 0.0716 1.0000
7.750 0.8642 0.02225 0.01424 -0.0040 0.0672 1.0000
8.000 0.8794 0.02286 0.01495 -0.0017 0.0629 1.0000
8.250 0.8948 0.02399 0.01602 0.0002 0.0588 1.0000
8.500 0.9095 0.02496 0.01718 0.0026 0.0551 1.0000
8.750 0.9237 0.02580 0.01813 0.0050 0.0519 1.0000
9.000 0.9378 0.02676 0.01905 0.0071 0.0489 1.0000
9.250 0.9504 0.02838 0.02087 0.0096 0.0461 1.0000
9.500 0.9618 0.02942 0.02212 0.0124 0.0438 1.0000
9.750 0.9730 0.03057 0.02341 0.0150 0.0419 1.0000
10.000 0.9846 0.03173 0.02460 0.0174 0.0402 1.0000
10.250 0.9933 0.03440 0.02740 0.0197 0.0385 1.0000
10.500 0.9951 0.03557 0.02889 0.0239 0.0374 1.0000
10.750 0.9955 0.03718 0.03078 0.0279 0.0362 1.0000
11.000 0.9947 0.03892 0.03276 0.0318 0.0352 1.0000
11.250 0.9909 0.04078 0.03482 0.0360 0.0344 1.0000
11.500 0.9849 0.04240 0.03659 0.0404 0.0338 1.0000
11.750 0.9774 0.04425 0.03860 0.0445 0.0334 1.0000
12.000 0.9663 0.04644 0.04098 0.0483 0.0331 1.0000
12.250 0.9561 0.04869 0.04338 0.0514 0.0327 1.0000
12.500 0.9399 0.05165 0.04654 0.0539 0.0325 1.0000
12.750 0.9262 0.05457 0.04961 0.0555 0.0323 1.0000
13.000 0.8550 0.06405 0.05969 0.0542 0.0338 1.0000
13.250 0.7994 0.07476 0.07071 0.0479 0.0350 1.0000
13.500 0.7366 0.09096 0.08710 0.0363 0.0367 1.0000
13.750 0.6966 0.10453 0.10067 0.0287 0.0381 1.0000
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Polar data table (+)
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