NACA 64(2)-415 (naca642415-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: NACA 64(2)-415 (naca642415-il) Reynolds number: 50,000 Max Cl/Cd: 27.25 at α=9.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-naca642415-il-50000.txt Download as CSV file: xf-naca642415-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: NACA 64(2)-415
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.750 -0.3371 0.10783 0.10061 -0.0284 1.0000 0.3655
-9.500 -0.4969 0.08164 0.07492 -0.0560 1.0000 0.1729
-9.250 -0.5063 0.07719 0.07054 -0.0559 1.0000 0.1661
-9.000 -0.6108 0.07306 0.06659 -0.0527 1.0000 0.1572
-8.750 -0.6327 0.07026 0.06376 -0.0498 1.0000 0.1532
-8.500 -0.6495 0.06728 0.06077 -0.0470 1.0000 0.1503
-8.250 -0.6745 0.06399 0.05736 -0.0442 1.0000 0.1470
-8.000 -0.7193 0.06009 0.05261 -0.0415 1.0000 0.1400
-7.750 -0.7161 0.05673 0.04914 -0.0399 1.0000 0.1390
-7.500 -0.7148 0.05362 0.04575 -0.0384 1.0000 0.1385
-7.250 -0.7108 0.05067 0.04243 -0.0371 1.0000 0.1386
-7.000 -0.7025 0.04785 0.03922 -0.0360 1.0000 0.1387
-6.750 -0.6906 0.04519 0.03616 -0.0350 1.0000 0.1389
-6.500 -0.6756 0.04277 0.03332 -0.0342 1.0000 0.1392
-6.250 -0.6589 0.04044 0.03071 -0.0335 1.0000 0.1415
-6.000 -0.6414 0.03868 0.02894 -0.0326 1.0000 0.1462
-5.750 -0.6228 0.03710 0.02711 -0.0318 1.0000 0.1504
-5.500 -0.6030 0.03567 0.02530 -0.0308 1.0000 0.1546
-5.250 -0.5845 0.03427 0.02397 -0.0297 1.0000 0.1617
-5.000 -0.5651 0.03328 0.02278 -0.0286 1.0000 0.1708
-4.750 -0.5473 0.03218 0.02188 -0.0270 1.0000 0.1810
-4.500 -0.5298 0.03125 0.02106 -0.0255 1.0000 0.1961
-4.250 -0.5124 0.03024 0.02014 -0.0241 1.0000 0.2194
-4.000 -0.4951 0.02856 0.01905 -0.0235 1.0000 0.2687
-3.750 -0.4942 0.02783 0.02069 -0.0166 1.0000 0.5819
-3.500 -0.4959 0.02991 0.02276 -0.0076 1.0000 0.6581
-3.250 -0.4968 0.03136 0.02419 0.0006 1.0000 0.6962
-3.000 -0.4912 0.03277 0.02550 0.0074 0.9970 0.7318
-2.750 -0.4812 0.03408 0.02669 0.0134 0.9919 0.7661
-2.500 -0.4715 0.03506 0.02754 0.0191 0.9868 0.7991
-2.250 -0.4592 0.03614 0.02851 0.0249 0.9817 0.8393
-2.000 -0.3803 0.03877 0.03078 0.0219 0.9741 0.8981
-1.750 -0.3181 0.03943 0.03110 0.0146 0.9680 0.9189
-1.500 -0.2576 0.03972 0.03111 0.0066 0.9619 0.9303
-1.250 -0.1950 0.04019 0.03131 -0.0021 0.9557 0.9404
-1.000 -0.1618 0.04015 0.03113 -0.0056 0.9504 0.9501
-0.750 -0.1258 0.04031 0.03114 -0.0097 0.9455 0.9599
-0.500 -0.0663 0.04088 0.03153 -0.0181 0.9401 0.9682
-0.250 -0.0348 0.04100 0.03156 -0.0216 0.9356 0.9766
0.000 0.0031 0.04132 0.03179 -0.0263 0.9307 0.9852
0.250 0.0494 0.04188 0.03226 -0.0326 0.9261 0.9937
0.500 0.0810 0.04238 0.03269 -0.0363 0.9221 1.0000
0.750 0.0722 0.04241 0.03270 -0.0329 0.9204 1.0000
1.000 0.0630 0.04241 0.03268 -0.0295 0.9200 1.0000
1.250 0.0525 0.04236 0.03262 -0.0260 0.9211 1.0000
1.500 -0.1326 0.03630 0.02678 0.0071 1.0000 1.0000
1.750 -0.1243 0.03611 0.02651 0.0074 1.0000 1.0000
2.000 -0.1079 0.03637 0.02670 0.0062 1.0000 1.0000
2.250 -0.0870 0.03694 0.02719 0.0043 1.0000 1.0000
2.500 -0.0638 0.03772 0.02789 0.0021 1.0000 1.0000
2.750 -0.0400 0.03865 0.02874 -0.0002 1.0000 1.0000
3.000 -0.0160 0.03968 0.02971 -0.0024 1.0000 1.0000
3.250 0.0075 0.04080 0.03076 -0.0045 1.0000 1.0000
3.500 0.0304 0.04198 0.03190 -0.0065 1.0000 1.0000
3.750 0.0526 0.04323 0.03310 -0.0083 1.0000 1.0000
4.000 0.0739 0.04453 0.03437 -0.0099 1.0000 1.0000
4.250 0.0947 0.04590 0.03572 -0.0115 0.9999 1.0000
4.500 0.1327 0.04852 0.03833 -0.0164 0.9898 1.0000
4.750 0.1698 0.05113 0.04096 -0.0211 0.9767 1.0000
5.000 0.2043 0.05360 0.04346 -0.0252 0.9618 1.0000
5.250 0.2368 0.05600 0.04589 -0.0288 0.9461 1.0000
5.500 0.2684 0.05839 0.04835 -0.0322 0.9293 1.0000
5.750 0.2990 0.06079 0.05081 -0.0353 0.9118 1.0000
6.000 0.3300 0.06329 0.05339 -0.0383 0.8938 1.0000
6.250 0.3653 0.06631 0.05651 -0.0419 0.8748 1.0000
6.500 0.3892 0.06849 0.05878 -0.0436 0.8563 1.0000
6.750 0.4063 0.06993 0.06032 -0.0441 0.8331 1.0000
7.000 0.4502 0.07328 0.06382 -0.0481 0.8065 1.0000
7.250 0.5727 0.06964 0.06047 -0.0497 0.6724 1.0000
7.500 0.6009 0.07044 0.06143 -0.0497 0.6475 1.0000
7.750 0.6359 0.07087 0.06204 -0.0497 0.6217 1.0000
8.000 0.7001 0.06936 0.06085 -0.0501 0.5943 1.0000
8.250 0.7146 0.06983 0.06148 -0.0485 0.5673 1.0000
8.500 0.7613 0.06762 0.05957 -0.0468 0.5379 1.0000
8.750 0.8447 0.05984 0.05230 -0.0432 0.5042 1.0000
9.000 0.9879 0.03842 0.03168 -0.0329 0.4313 1.0000
9.250 0.9959 0.03655 0.02823 -0.0253 0.2875 1.0000
9.500 0.9925 0.03940 0.03018 -0.0221 0.2332 1.0000
9.750 1.0067 0.04176 0.03211 -0.0203 0.1945 1.0000
10.000 1.0494 0.04363 0.03368 -0.0203 0.1636 1.0000
10.250 1.1150 0.04632 0.03619 -0.0232 0.1415 1.0000
10.500 1.1684 0.04991 0.03978 -0.0263 0.1291 1.0000
10.750 1.1785 0.05261 0.04295 -0.0246 0.1241 1.0000
11.000 1.2061 0.05596 0.04645 -0.0250 0.1188 1.0000
11.250 1.2289 0.06025 0.05090 -0.0253 0.1154 1.0000
11.500 1.2232 0.06343 0.05453 -0.0226 0.1143 1.0000
11.750 1.2118 0.06663 0.05810 -0.0196 0.1135 1.0000
12.000 1.1969 0.07010 0.06190 -0.0170 0.1129 1.0000
12.250 1.1790 0.07395 0.06605 -0.0149 0.1128 1.0000
12.500 1.1581 0.07823 0.07061 -0.0135 0.1130 1.0000
12.750 1.1352 0.08303 0.07566 -0.0129 0.1135 1.0000
13.000 1.1106 0.08846 0.08130 -0.0131 0.1141 1.0000
13.250 1.0867 0.09448 0.08750 -0.0142 0.1149 1.0000
13.500 1.0651 0.10105 0.09420 -0.0159 0.1156 1.0000
13.750 0.9209 0.12570 0.11915 -0.0327 0.1313 1.0000
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Polar data table (+)
Polar graphs
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