NACA 0010-64 (naca001064-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: NACA 0010-64 (naca001064-il) Reynolds number: 500,000 Max Cl/Cd: 49.19 at α=5.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-naca001064-il-500000.txt Download as CSV file: xf-naca001064-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: NACA 0010-64
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
------ -------- --------- --------- -------- -------- --------
-13.250 -0.6948 0.08601 0.08371 -0.0253 1.0000 0.0200
-13.000 -0.7777 0.10123 0.09887 -0.0092 1.0000 0.0196
-12.750 -0.8634 0.07215 0.06964 -0.0290 1.0000 0.0182
-12.500 -0.9109 0.05996 0.05719 -0.0381 1.0000 0.0176
-12.250 -0.9548 0.05178 0.04872 -0.0405 1.0000 0.0174
-12.000 -0.9836 0.04678 0.04344 -0.0392 1.0000 0.0174
-11.750 -1.0042 0.04313 0.03952 -0.0361 1.0000 0.0177
-11.500 -1.0203 0.04009 0.03620 -0.0319 1.0000 0.0180
-11.250 -1.0286 0.03708 0.03286 -0.0282 1.0000 0.0184
-11.000 -1.0298 0.03448 0.02990 -0.0250 1.0000 0.0189
-10.750 -1.0232 0.03284 0.02795 -0.0224 1.0000 0.0193
-10.500 -1.0234 0.02932 0.02411 -0.0192 1.0000 0.0199
-10.250 -1.0091 0.02827 0.02300 -0.0176 1.0000 0.0205
-10.000 -0.9936 0.02756 0.02223 -0.0159 1.0000 0.0211
-9.750 -0.9780 0.02682 0.02140 -0.0142 1.0000 0.0218
-9.500 -0.9625 0.02603 0.02050 -0.0123 1.0000 0.0227
-9.250 -0.9470 0.02521 0.01950 -0.0102 1.0000 0.0237
-9.000 -0.9307 0.02477 0.01889 -0.0082 1.0000 0.0244
-8.750 -0.9189 0.02220 0.01611 -0.0059 1.0000 0.0255
-8.500 -0.9022 0.02140 0.01529 -0.0041 1.0000 0.0264
-8.250 -0.8850 0.02081 0.01464 -0.0024 1.0000 0.0273
-8.000 -0.8674 0.02027 0.01403 -0.0006 1.0000 0.0285
-7.750 -0.8496 0.01974 0.01341 0.0012 1.0000 0.0297
-7.500 -0.8312 0.01936 0.01293 0.0030 1.0000 0.0306
-7.250 -0.8143 0.01795 0.01138 0.0049 1.0000 0.0318
-7.000 -0.7973 0.01693 0.01035 0.0067 1.0000 0.0331
-6.750 -0.7789 0.01646 0.00986 0.0083 1.0000 0.0344
-6.500 -0.7600 0.01602 0.00939 0.0099 1.0000 0.0358
-6.250 -0.7410 0.01554 0.00886 0.0115 1.0000 0.0370
-6.000 -0.7217 0.01510 0.00836 0.0130 1.0000 0.0380
-5.750 -0.7015 0.01483 0.00803 0.0144 1.0000 0.0389
-5.500 -0.6775 0.01377 0.00693 0.0147 0.9991 0.0409
-5.250 -0.6450 0.01322 0.00637 0.0134 0.9971 0.0428
-5.000 -0.6115 0.01283 0.00597 0.0119 0.9953 0.0449
-4.750 -0.5775 0.01249 0.00559 0.0103 0.9936 0.0472
-4.500 -0.5456 0.01212 0.00519 0.0093 0.9908 0.0489
-4.250 -0.5133 0.01162 0.00470 0.0081 0.9882 0.0536
-4.000 -0.4788 0.01134 0.00441 0.0064 0.9860 0.0591
-3.750 -0.4443 0.01086 0.00407 0.0047 0.9842 0.0793
-3.500 -0.4126 0.01029 0.00378 0.0035 0.9817 0.1356
-3.250 -0.3837 0.00972 0.00353 0.0028 0.9776 0.2087
-3.000 -0.3529 0.00900 0.00328 0.0016 0.9746 0.3188
-2.750 -0.3231 0.00803 0.00304 0.0005 0.9723 0.4907
-2.500 -0.2913 0.00736 0.00291 -0.0007 0.9705 0.6261
-2.250 -0.2657 0.00703 0.00286 -0.0001 0.9650 0.6993
-2.000 -0.2338 0.00681 0.00283 -0.0009 0.9616 0.7527
-1.750 -0.2002 0.00667 0.00280 -0.0019 0.9588 0.7887
-1.500 -0.1666 0.00657 0.00279 -0.0029 0.9564 0.8212
-1.250 -0.1404 0.00652 0.00281 -0.0022 0.9501 0.8438
-1.000 -0.1101 0.00647 0.00279 -0.0024 0.9455 0.8608
-0.750 -0.0791 0.00644 0.00279 -0.0026 0.9418 0.8791
-0.500 -0.0548 0.00646 0.00285 -0.0014 0.9343 0.8956
-0.250 -0.0265 0.00649 0.00290 -0.0010 0.9287 0.9091
0.000 0.0000 0.00653 0.00296 0.0000 0.9200 0.9201
0.250 0.0264 0.00649 0.00290 0.0010 0.9090 0.9287
0.500 0.0547 0.00646 0.00285 0.0014 0.8955 0.9343
0.750 0.0791 0.00644 0.00279 0.0027 0.8791 0.9418
1.000 0.1101 0.00647 0.00279 0.0024 0.8608 0.9455
1.250 0.1404 0.00652 0.00281 0.0022 0.8437 0.9501
1.500 0.1666 0.00657 0.00279 0.0029 0.8212 0.9564
1.750 0.2002 0.00667 0.00280 0.0019 0.7888 0.9588
2.000 0.2338 0.00681 0.00283 0.0009 0.7528 0.9616
2.250 0.2657 0.00703 0.00286 0.0001 0.6992 0.9650
2.500 0.2913 0.00735 0.00291 0.0007 0.6268 0.9705
2.750 0.3231 0.00804 0.00304 -0.0005 0.4903 0.9723
3.000 0.3529 0.00900 0.00328 -0.0016 0.3187 0.9747
3.250 0.3837 0.00972 0.00353 -0.0028 0.2087 0.9776
3.500 0.4126 0.01029 0.00378 -0.0035 0.1356 0.9817
3.750 0.4443 0.01086 0.00407 -0.0047 0.0793 0.9842
4.000 0.4788 0.01134 0.00441 -0.0064 0.0591 0.9860
4.250 0.5133 0.01162 0.00470 -0.0081 0.0536 0.9882
4.500 0.5456 0.01212 0.00518 -0.0093 0.0490 0.9908
4.750 0.5775 0.01249 0.00559 -0.0103 0.0472 0.9936
5.000 0.6115 0.01283 0.00596 -0.0119 0.0449 0.9953
5.250 0.6451 0.01322 0.00637 -0.0134 0.0428 0.9971
5.500 0.6774 0.01377 0.00693 -0.0147 0.0409 0.9991
5.750 0.7014 0.01482 0.00803 -0.0143 0.0389 1.0000
6.000 0.7215 0.01509 0.00836 -0.0130 0.0380 1.0000
6.250 0.7409 0.01554 0.00885 -0.0114 0.0370 1.0000
6.500 0.7599 0.01601 0.00938 -0.0099 0.0358 1.0000
6.750 0.7788 0.01645 0.00985 -0.0083 0.0344 1.0000
7.000 0.7972 0.01692 0.01034 -0.0066 0.0331 1.0000
7.250 0.8141 0.01795 0.01138 -0.0048 0.0318 1.0000
7.500 0.8311 0.01936 0.01292 -0.0030 0.0306 1.0000
7.750 0.8494 0.01974 0.01341 -0.0012 0.0297 1.0000
8.000 0.8673 0.02026 0.01402 0.0006 0.0285 1.0000
8.250 0.8849 0.02080 0.01464 0.0024 0.0273 1.0000
8.500 0.9021 0.02140 0.01528 0.0042 0.0264 1.0000
8.750 0.9188 0.02220 0.01611 0.0059 0.0255 1.0000
9.000 0.9306 0.02477 0.01889 0.0082 0.0244 1.0000
9.250 0.9470 0.02521 0.01951 0.0103 0.0237 1.0000
9.500 0.9624 0.02604 0.02051 0.0123 0.0227 1.0000
9.750 0.9779 0.02683 0.02142 0.0142 0.0218 1.0000
10.000 0.9936 0.02757 0.02224 0.0159 0.0211 1.0000
10.250 1.0091 0.02828 0.02302 0.0176 0.0205 1.0000
10.500 1.0234 0.02933 0.02412 0.0192 0.0199 1.0000
10.750 1.0233 0.03283 0.02795 0.0224 0.0193 1.0000
11.000 1.0298 0.03449 0.02991 0.0250 0.0189 1.0000
11.250 1.0288 0.03709 0.03287 0.0282 0.0184 1.0000
11.500 1.0205 0.04011 0.03623 0.0318 0.0180 1.0000
11.750 1.0043 0.04318 0.03957 0.0360 0.0177 1.0000
12.000 0.9846 0.04675 0.04340 0.0390 0.0174 1.0000
12.250 0.9550 0.05185 0.04879 0.0404 0.0174 1.0000
12.500 0.9101 0.06022 0.05747 0.0378 0.0177 1.0000
12.750 0.8630 0.07253 0.07003 0.0284 0.0182 1.0000
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