NACA 63(2)-215 MOD B (n63215b-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: NACA 63(2)-215 MOD B (n63215b-il) Reynolds number: 200,000 Max Cl/Cd: 44.41 at α=7.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-n63215b-il-200000.txt Download as CSV file: xf-n63215b-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: NACA 63(2)-215 MOD B
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
------ -------- --------- --------- -------- -------- --------
-14.000 -0.6752 0.09563 0.09149 -0.0336 1.0000 0.0422
-13.750 -0.6997 0.08700 0.08280 -0.0387 1.0000 0.0415
-13.500 -0.7356 0.07778 0.07342 -0.0446 1.0000 0.0408
-13.250 -0.7705 0.06996 0.06540 -0.0492 1.0000 0.0401
-13.000 -0.8044 0.06319 0.05839 -0.0524 1.0000 0.0394
-12.750 -0.8352 0.05751 0.05243 -0.0541 1.0000 0.0389
-12.500 -0.8614 0.05282 0.04747 -0.0544 1.0000 0.0386
-12.250 -0.8792 0.04919 0.04358 -0.0537 1.0000 0.0385
-12.000 -0.8923 0.04606 0.04021 -0.0523 1.0000 0.0385
-11.750 -0.8990 0.04355 0.03749 -0.0504 1.0000 0.0386
-11.500 -0.9021 0.04137 0.03511 -0.0482 1.0000 0.0389
-11.250 -0.8998 0.03926 0.03282 -0.0462 1.0000 0.0394
-11.000 -0.8935 0.03726 0.03060 -0.0445 1.0000 0.0401
-10.750 -0.8849 0.03544 0.02856 -0.0428 1.0000 0.0410
-10.500 -0.8758 0.03396 0.02682 -0.0410 1.0000 0.0421
-10.250 -0.8624 0.03188 0.02454 -0.0397 1.0000 0.0435
-10.000 -0.8432 0.03045 0.02318 -0.0389 1.0000 0.0449
-9.750 -0.8280 0.02942 0.02212 -0.0374 1.0000 0.0463
-9.500 -0.8160 0.02841 0.02106 -0.0353 1.0000 0.0476
-9.250 -0.8140 0.02772 0.02030 -0.0315 1.0000 0.0487
-9.000 -0.8182 0.02726 0.01974 -0.0268 1.0000 0.0495
-8.750 -0.7858 0.02567 0.01809 -0.0283 0.9959 0.0515
-8.500 -0.7484 0.02454 0.01704 -0.0309 0.9904 0.0543
-8.250 -0.7107 0.02370 0.01614 -0.0334 0.9841 0.0578
-8.000 -0.6717 0.02241 0.01484 -0.0361 0.9800 0.0614
-7.750 -0.6361 0.02145 0.01395 -0.0383 0.9734 0.0651
-7.500 -0.5969 0.02059 0.01304 -0.0409 0.9684 0.0689
-7.250 -0.5644 0.01939 0.01191 -0.0425 0.9615 0.0729
-7.000 -0.5301 0.01856 0.01110 -0.0444 0.9547 0.0783
-6.750 -0.5021 0.01768 0.01026 -0.0451 0.9458 0.0856
-6.500 -0.4734 0.01683 0.00945 -0.0458 0.9378 0.0975
-6.250 -0.4540 0.01594 0.00871 -0.0449 0.9268 0.1227
-6.000 -0.4391 0.01460 0.00787 -0.0438 0.9169 0.1998
-5.750 -0.4250 0.01333 0.00729 -0.0424 0.9077 0.3302
-5.500 -0.4049 0.01289 0.00721 -0.0412 0.8987 0.4166
-5.250 -0.3799 0.01280 0.00719 -0.0404 0.8917 0.4621
-5.000 -0.3546 0.01282 0.00720 -0.0397 0.8838 0.4924
-4.750 -0.3287 0.01286 0.00726 -0.0389 0.8769 0.5151
-4.500 -0.3022 0.01296 0.00734 -0.0383 0.8707 0.5358
-4.250 -0.2758 0.01309 0.00744 -0.0377 0.8635 0.5546
-4.000 -0.2493 0.01322 0.00753 -0.0368 0.8579 0.5724
-3.750 -0.2235 0.01336 0.00769 -0.0359 0.8490 0.5877
-3.500 -0.1977 0.01344 0.00775 -0.0346 0.8415 0.6012
-3.250 -0.1719 0.01351 0.00779 -0.0337 0.8313 0.6129
-3.000 -0.1458 0.01358 0.00778 -0.0325 0.8237 0.6260
-2.750 -0.1201 0.01371 0.00793 -0.0314 0.8133 0.6386
-2.500 -0.0934 0.01371 0.00791 -0.0304 0.8061 0.6466
-2.250 -0.0660 0.01368 0.00784 -0.0302 0.7979 0.6548
-2.000 -0.0385 0.01365 0.00778 -0.0295 0.7920 0.6619
-1.750 -0.0114 0.01365 0.00778 -0.0291 0.7834 0.6697
-1.500 0.0164 0.01354 0.00759 -0.0286 0.7762 0.6764
-1.250 0.0434 0.01350 0.00758 -0.0281 0.7671 0.6823
-1.000 0.0718 0.01337 0.00733 -0.0278 0.7594 0.6904
-0.750 0.0984 0.01331 0.00732 -0.0271 0.7494 0.6954
-0.500 0.1261 0.01322 0.00716 -0.0265 0.7408 0.7026
-0.250 0.1535 0.01310 0.00704 -0.0261 0.7296 0.7095
0.000 0.1804 0.01302 0.00696 -0.0254 0.7187 0.7153
0.250 0.2088 0.01288 0.00673 -0.0251 0.7074 0.7230
0.500 0.2353 0.01275 0.00662 -0.0243 0.6941 0.7282
0.750 0.2623 0.01265 0.00652 -0.0237 0.6791 0.7352
1.000 0.2896 0.01253 0.00637 -0.0232 0.6623 0.7423
1.250 0.3159 0.01244 0.00626 -0.0224 0.6435 0.7484
1.500 0.3433 0.01236 0.00612 -0.0220 0.6175 0.7567
1.750 0.3675 0.01233 0.00603 -0.0207 0.5793 0.7626
2.000 0.3904 0.01249 0.00589 -0.0194 0.4981 0.7709
2.250 0.4065 0.01324 0.00597 -0.0174 0.3824 0.7777
2.500 0.4269 0.01388 0.00629 -0.0162 0.3467 0.7852
2.750 0.4500 0.01433 0.00660 -0.0154 0.3240 0.7927
3.000 0.4731 0.01470 0.00687 -0.0145 0.3063 0.8003
3.250 0.4977 0.01500 0.00710 -0.0140 0.2908 0.8085
3.500 0.5210 0.01528 0.00735 -0.0131 0.2774 0.8158
3.750 0.5456 0.01561 0.00758 -0.0126 0.2659 0.8243
4.000 0.5682 0.01589 0.00783 -0.0115 0.2559 0.8322
4.250 0.5924 0.01618 0.00811 -0.0109 0.2466 0.8413
4.500 0.6144 0.01650 0.00838 -0.0097 0.2387 0.8504
4.750 0.6372 0.01677 0.00868 -0.0087 0.2310 0.8598
5.000 0.6600 0.01707 0.00895 -0.0078 0.2240 0.8701
5.250 0.6805 0.01740 0.00928 -0.0063 0.2177 0.8796
5.500 0.7020 0.01762 0.00953 -0.0051 0.2110 0.8908
5.750 0.7226 0.01805 0.00986 -0.0038 0.2051 0.9028
6.000 0.7412 0.01820 0.01013 -0.0019 0.1998 0.9154
6.250 0.7600 0.01840 0.01036 -0.0001 0.1946 0.9296
6.500 0.7817 0.01880 0.01070 0.0009 0.1897 0.9456
6.750 0.8098 0.01916 0.01115 0.0007 0.1845 0.9631
7.000 0.8468 0.01956 0.01157 -0.0015 0.1783 0.9807
7.250 0.8826 0.02028 0.01216 -0.0039 0.1725 1.0000
7.500 0.9081 0.02061 0.01261 -0.0043 0.1675 1.0000
7.750 0.9352 0.02106 0.01304 -0.0049 0.1627 1.0000
8.000 0.9633 0.02182 0.01366 -0.0057 0.1581 1.0000
8.250 0.9890 0.02240 0.01435 -0.0059 0.1543 1.0000
8.500 1.0144 0.02298 0.01498 -0.0061 0.1504 1.0000
8.750 1.0396 0.02355 0.01554 -0.0061 0.1469 1.0000
9.000 1.0660 0.02438 0.01628 -0.0065 0.1436 1.0000
9.250 1.0904 0.02531 0.01728 -0.0064 0.1406 1.0000
9.500 1.1120 0.02596 0.01806 -0.0060 0.1375 1.0000
9.750 1.1338 0.02659 0.01876 -0.0055 0.1344 1.0000
10.000 1.1560 0.02720 0.01934 -0.0052 0.1315 1.0000
10.250 1.1805 0.02819 0.02026 -0.0053 0.1286 1.0000
10.500 1.2011 0.02935 0.02154 -0.0048 0.1263 1.0000
10.750 1.2184 0.03020 0.02256 -0.0038 0.1241 1.0000
11.000 1.2354 0.03111 0.02360 -0.0029 0.1217 1.0000
11.250 1.2527 0.03197 0.02454 -0.0020 0.1194 1.0000
11.500 1.2708 0.03282 0.02543 -0.0012 0.1174 1.0000
11.750 1.2906 0.03379 0.02637 -0.0007 0.1155 1.0000
12.000 1.3111 0.03595 0.02857 -0.0008 0.1131 1.0000
12.250 1.3162 0.03698 0.02981 0.0015 0.1120 1.0000
12.500 1.3193 0.03820 0.03123 0.0038 0.1105 1.0000
12.750 1.3224 0.03955 0.03275 0.0058 0.1089 1.0000
13.000 1.3252 0.04103 0.03439 0.0075 0.1073 1.0000
13.250 1.3285 0.04263 0.03611 0.0089 0.1059 1.0000
13.500 1.3325 0.04427 0.03786 0.0101 0.1047 1.0000
13.750 1.3380 0.04589 0.03956 0.0110 0.1035 1.0000
14.000 1.3454 0.04753 0.04126 0.0117 0.1024 1.0000
14.250 1.3536 0.04945 0.04323 0.0122 0.1012 1.0000
14.500 1.3519 0.05294 0.04684 0.0126 0.1000 1.0000
14.750 1.3315 0.05698 0.05113 0.0131 0.0994 1.0000
15.000 1.3066 0.06137 0.05578 0.0130 0.0990 1.0000
15.250 1.2715 0.06737 0.06207 0.0116 0.0987 1.0000
15.500 1.2140 0.07700 0.07203 0.0076 0.0986 1.0000
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