NACA 22112 (naca22112-jf) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: NACA 22112 (naca22112-jf) Reynolds number: 500,000 Max Cl/Cd: 67.66 at α=9.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-naca22112-jf-500000.txt Download as CSV file: xf-naca22112-jf-500000.csv |
XFOIL Version 6.96
Calculated polar for: NACA 22112
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
------ -------- --------- --------- -------- -------- --------
-14.750 -0.4730 0.14524 0.14292 0.0021 1.0000 0.0244
-8.500 -0.7876 0.03141 0.02619 -0.0104 1.0000 0.0242
-8.250 -0.7756 0.02865 0.02316 -0.0080 1.0000 0.0241
-8.000 -0.7617 0.02641 0.02062 -0.0056 1.0000 0.0242
-7.750 -0.7473 0.02396 0.01789 -0.0034 1.0000 0.0247
-7.500 -0.7286 0.02283 0.01677 -0.0020 1.0000 0.0252
-7.250 -0.7091 0.02240 0.01638 -0.0006 1.0000 0.0258
-7.000 -0.6904 0.02144 0.01533 0.0011 1.0000 0.0264
-6.750 -0.6716 0.02022 0.01398 0.0030 1.0000 0.0268
-6.500 -0.6524 0.01912 0.01277 0.0047 1.0000 0.0273
-6.250 -0.6331 0.01817 0.01172 0.0065 1.0000 0.0280
-6.000 -0.6139 0.01745 0.01089 0.0083 1.0000 0.0286
-5.750 -0.5854 0.01633 0.00971 0.0080 0.9987 0.0294
-5.500 -0.5488 0.01559 0.00903 0.0060 0.9960 0.0307
-5.250 -0.5110 0.01500 0.00844 0.0039 0.9935 0.0320
-5.000 -0.4752 0.01435 0.00776 0.0022 0.9896 0.0333
-4.750 -0.4369 0.01389 0.00726 0.0002 0.9860 0.0343
-4.500 -0.4004 0.01287 0.00630 -0.0019 0.9832 0.0363
-4.250 -0.3651 0.01244 0.00589 -0.0034 0.9773 0.0384
-4.000 -0.3275 0.01201 0.00545 -0.0054 0.9726 0.0403
-3.750 -0.2960 0.01133 0.00478 -0.0061 0.9643 0.0426
-3.500 -0.2623 0.01094 0.00441 -0.0072 0.9561 0.0456
-3.250 -0.2336 0.01068 0.00413 -0.0070 0.9429 0.0483
-3.000 -0.2073 0.01021 0.00365 -0.0064 0.9279 0.0524
-2.750 -0.1809 0.00996 0.00338 -0.0057 0.9111 0.0568
-2.500 -0.1556 0.00965 0.00304 -0.0048 0.8923 0.0644
-2.250 -0.1306 0.00937 0.00274 -0.0039 0.8709 0.0810
-2.000 -0.1182 0.00749 0.00224 -0.0015 0.8463 0.4441
-1.750 -0.0980 0.00694 0.00209 0.0002 0.8172 0.5745
-1.500 -0.0759 0.00667 0.00201 0.0018 0.7847 0.6534
-1.250 -0.0523 0.00654 0.00197 0.0031 0.7556 0.7106
-1.000 -0.0276 0.00646 0.00196 0.0041 0.7298 0.7562
-0.750 -0.0028 0.00644 0.00196 0.0052 0.7036 0.7959
-0.500 0.0222 0.00648 0.00199 0.0062 0.6755 0.8292
-0.250 0.0477 0.00655 0.00202 0.0072 0.6485 0.8569
0.250 0.0982 0.00679 0.00218 0.0093 0.5968 0.9055
0.500 0.1244 0.00697 0.00225 0.0100 0.5696 0.9207
0.750 0.1520 0.00715 0.00231 0.0104 0.5408 0.9316
1.000 0.1792 0.00733 0.00238 0.0108 0.5131 0.9426
1.250 0.2095 0.00754 0.00247 0.0106 0.4857 0.9508
1.500 0.2397 0.00776 0.00255 0.0103 0.4575 0.9587
1.750 0.2740 0.00800 0.00266 0.0090 0.4264 0.9641
2.000 0.3054 0.00825 0.00276 0.0083 0.3951 0.9710
2.250 0.3443 0.00852 0.00288 0.0059 0.3618 0.9734
2.500 0.3824 0.00880 0.00300 0.0037 0.3288 0.9765
2.750 0.4174 0.00910 0.00313 0.0020 0.2961 0.9810
3.000 0.4535 0.00941 0.00327 0.0001 0.2633 0.9844
3.250 0.4915 0.00971 0.00342 -0.0022 0.2349 0.9870
3.500 0.5281 0.01002 0.00359 -0.0043 0.2137 0.9902
3.750 0.5634 0.01030 0.00377 -0.0060 0.1988 0.9938
4.000 0.6015 0.01051 0.00393 -0.0083 0.1873 0.9959
4.250 0.6387 0.01075 0.00412 -0.0105 0.1785 0.9984
4.500 0.6713 0.01096 0.00429 -0.0117 0.1718 1.0000
4.750 0.6933 0.01122 0.00450 -0.0107 0.1661 1.0000
5.000 0.7161 0.01135 0.00466 -0.0098 0.1620 1.0000
5.250 0.7383 0.01155 0.00484 -0.0089 0.1576 1.0000
5.500 0.7596 0.01186 0.00511 -0.0077 0.1531 1.0000
5.750 0.7816 0.01208 0.00536 -0.0067 0.1500 1.0000
6.000 0.8039 0.01226 0.00556 -0.0056 0.1467 1.0000
6.250 0.8257 0.01248 0.00579 -0.0046 0.1432 1.0000
6.500 0.8465 0.01283 0.00610 -0.0033 0.1397 1.0000
6.750 0.8674 0.01318 0.00647 -0.0021 0.1365 1.0000
7.000 0.8899 0.01337 0.00670 -0.0011 0.1338 1.0000
7.250 0.9120 0.01360 0.00697 -0.0001 0.1309 1.0000
7.500 0.9337 0.01388 0.00725 0.0010 0.1279 1.0000
7.750 0.9535 0.01440 0.00773 0.0023 0.1241 1.0000
8.000 0.9758 0.01465 0.00805 0.0033 0.1219 1.0000
8.250 0.9986 0.01487 0.00832 0.0042 0.1192 1.0000
8.500 1.0211 0.01511 0.00859 0.0051 0.1163 1.0000
8.750 1.0429 0.01545 0.00892 0.0060 0.1133 1.0000
9.000 1.0629 0.01602 0.00949 0.0072 0.1099 1.0000
9.250 1.0866 0.01620 0.00976 0.0078 0.1076 1.0000
9.500 1.1100 0.01644 0.01005 0.0085 0.1046 1.0000
9.750 1.1326 0.01674 0.01036 0.0092 0.1016 1.0000
10.000 1.1522 0.01737 0.01098 0.0103 0.0980 1.0000
10.250 1.1762 0.01756 0.01127 0.0108 0.0956 1.0000
10.500 1.1995 0.01782 0.01159 0.0114 0.0925 1.0000
10.750 1.2212 0.01820 0.01197 0.0121 0.0892 1.0000
11.000 1.2409 0.01878 0.01257 0.0131 0.0860 1.0000
11.250 1.2637 0.01906 0.01295 0.0137 0.0831 1.0000
11.500 1.2851 0.01944 0.01336 0.0144 0.0798 1.0000
11.750 1.3021 0.02016 0.01406 0.0156 0.0761 1.0000
12.000 1.3241 0.02048 0.01450 0.0162 0.0733 1.0000
12.250 1.3436 0.02096 0.01502 0.0171 0.0700 1.0000
12.500 1.3578 0.02178 0.01582 0.0186 0.0665 1.0000
12.750 1.3765 0.02223 0.01640 0.0196 0.0638 1.0000
13.000 1.3906 0.02287 0.01708 0.0212 0.0607 1.0000
13.250 1.3992 0.02386 0.01808 0.0233 0.0577 1.0000
13.500 1.4138 0.02455 0.01888 0.0246 0.0550 1.0000
13.750 1.4240 0.02555 0.01992 0.0261 0.0522 1.0000
14.000 1.4293 0.02694 0.02136 0.0277 0.0496 1.0000
14.250 1.4403 0.02802 0.02256 0.0287 0.0472 1.0000
14.500 1.4462 0.02957 0.02416 0.0297 0.0449 1.0000
14.750 1.4458 0.03176 0.02641 0.0305 0.0428 1.0000
15.000 1.4527 0.03350 0.02828 0.0308 0.0410 1.0000
15.250 1.4546 0.03583 0.03071 0.0308 0.0393 1.0000
15.500 1.4507 0.03900 0.03395 0.0303 0.0378 1.0000
15.750 1.4429 0.04286 0.03793 0.0291 0.0365 1.0000
16.000 1.4407 0.04629 0.04151 0.0278 0.0354 1.0000
16.250 1.4339 0.05046 0.04582 0.0261 0.0343 1.0000
16.500 1.4218 0.05551 0.05100 0.0237 0.0335 1.0000
16.750 1.4049 0.06139 0.05700 0.0209 0.0329 1.0000
17.000 1.3835 0.06807 0.06381 0.0176 0.0324 1.0000
17.250 1.3589 0.07531 0.07118 0.0141 0.0321 1.0000
17.500 1.3327 0.08297 0.07896 0.0104 0.0318 1.0000
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