NACA 64-208 (naca64208-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA 64-208 (naca64208-il) Reynolds number: 100,000 Max Cl/Cd: 42.79 at α=3.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-naca64208-il-100000-n5.txt Download as CSV file: xf-naca64208-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NACA 64-208
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.500 -0.4604 0.09091 0.08620 -0.0152 1.0000 0.0308
-9.250 -0.4618 0.08622 0.08154 -0.0166 1.0000 0.0296
-9.000 -0.5515 0.09173 0.08678 -0.0153 1.0000 0.0307
-8.750 -0.5518 0.08720 0.08230 -0.0174 1.0000 0.0292
-8.500 -0.5544 0.08218 0.07733 -0.0207 1.0000 0.0280
-8.250 -0.5598 0.07672 0.07194 -0.0253 1.0000 0.0271
-8.000 -0.5672 0.07100 0.06621 -0.0301 1.0000 0.0261
-7.750 -0.5718 0.06506 0.06016 -0.0338 1.0000 0.0248
-7.500 -0.5756 0.05769 0.05242 -0.0370 1.0000 0.0228
-7.250 -0.5677 0.05339 0.04782 -0.0375 1.0000 0.0222
-7.000 -0.5580 0.04949 0.04361 -0.0376 1.0000 0.0220
-6.750 -0.5470 0.04555 0.03934 -0.0375 1.0000 0.0220
-6.500 -0.5367 0.04105 0.03449 -0.0373 1.0000 0.0224
-6.250 -0.5230 0.03842 0.03177 -0.0373 1.0000 0.0244
-6.000 -0.5059 0.03607 0.02917 -0.0368 1.0000 0.0265
-5.750 -0.4878 0.03289 0.02555 -0.0359 1.0000 0.0270
-5.500 -0.4681 0.02993 0.02213 -0.0349 1.0000 0.0274
-5.250 -0.4472 0.02739 0.01914 -0.0339 1.0000 0.0281
-5.000 -0.4253 0.02526 0.01658 -0.0328 1.0000 0.0294
-4.750 -0.4028 0.02396 0.01490 -0.0316 1.0000 0.0326
-4.500 -0.3806 0.02243 0.01310 -0.0305 1.0000 0.0337
-4.250 -0.3595 0.02046 0.01103 -0.0293 1.0000 0.0351
-4.000 -0.3387 0.01915 0.00969 -0.0282 1.0000 0.0370
-3.750 -0.3181 0.01814 0.00865 -0.0270 1.0000 0.0395
-3.500 -0.2974 0.01744 0.00785 -0.0259 1.0000 0.0449
-3.250 -0.2771 0.01658 0.00693 -0.0250 1.0000 0.0500
-3.000 -0.2493 0.01588 0.00613 -0.0254 0.9968 0.0570
-2.750 -0.2137 0.01511 0.00538 -0.0275 0.9897 0.0774
-2.500 -0.1815 0.01317 0.00461 -0.0298 0.9835 0.3203
-2.250 -0.1557 0.01209 0.00486 -0.0292 0.9763 0.6621
-2.000 -0.1327 0.01208 0.00520 -0.0267 0.9670 0.7764
-1.750 -0.1106 0.01220 0.00539 -0.0240 0.9574 0.8418
-1.500 -0.0763 0.01217 0.00523 -0.0250 0.9504 0.8598
-1.250 -0.0433 0.01212 0.00503 -0.0260 0.9416 0.8740
-1.000 -0.0096 0.01206 0.00487 -0.0271 0.9332 0.8881
-0.750 0.0258 0.01201 0.00473 -0.0286 0.9257 0.9022
-0.500 0.0594 0.01196 0.00462 -0.0297 0.9163 0.9171
-0.250 0.0967 0.01190 0.00450 -0.0316 0.9088 0.9313
0.000 0.1346 0.01185 0.00441 -0.0337 0.9001 0.9454
0.250 0.1745 0.01180 0.00434 -0.0363 0.8916 0.9592
0.500 0.2163 0.01175 0.00429 -0.0393 0.8839 0.9722
0.750 0.2565 0.01171 0.00427 -0.0421 0.8740 0.9878
1.000 0.2907 0.01171 0.00429 -0.0437 0.8637 1.0000
1.250 0.3161 0.01178 0.00438 -0.0434 0.8527 1.0000
1.500 0.3422 0.01185 0.00447 -0.0432 0.8420 1.0000
1.750 0.3676 0.01196 0.00463 -0.0429 0.8303 1.0000
2.000 0.3936 0.01209 0.00481 -0.0426 0.8192 1.0000
2.250 0.4201 0.01221 0.00504 -0.0424 0.8079 1.0000
2.500 0.4463 0.01231 0.00523 -0.0419 0.7949 1.0000
2.750 0.4721 0.01241 0.00543 -0.0413 0.7798 1.0000
3.000 0.4937 0.01225 0.00523 -0.0388 0.7371 1.0000
3.250 0.5117 0.01218 0.00480 -0.0352 0.6471 1.0000
3.500 0.5332 0.01246 0.00487 -0.0334 0.5635 1.0000
3.750 0.5488 0.01354 0.00500 -0.0309 0.3526 1.0000
4.000 0.5602 0.01605 0.00600 -0.0293 0.0944 1.0000
4.250 0.5820 0.01716 0.00695 -0.0285 0.0652 1.0000
4.500 0.6046 0.01809 0.00786 -0.0279 0.0514 1.0000
4.750 0.6276 0.01898 0.00896 -0.0271 0.0456 1.0000
5.000 0.6495 0.02008 0.01012 -0.0262 0.0416 1.0000
5.250 0.6704 0.02171 0.01173 -0.0252 0.0389 1.0000
5.500 0.6950 0.02282 0.01301 -0.0246 0.0357 1.0000
5.750 0.7196 0.02414 0.01447 -0.0240 0.0323 1.0000
6.000 0.7445 0.02586 0.01633 -0.0235 0.0306 1.0000
6.250 0.7693 0.02787 0.01852 -0.0229 0.0292 1.0000
6.500 0.7932 0.03036 0.02132 -0.0224 0.0282 1.0000
7.000 0.8353 0.03583 0.02769 -0.0205 0.0251 1.0000
7.250 0.8535 0.03893 0.03132 -0.0193 0.0240 1.0000
7.500 0.8681 0.04264 0.03556 -0.0179 0.0235 1.0000
7.750 0.8791 0.04670 0.04012 -0.0165 0.0233 1.0000
8.000 0.8864 0.05105 0.04492 -0.0151 0.0232 1.0000
8.250 0.8899 0.05551 0.04979 -0.0139 0.0231 1.0000
8.500 0.8896 0.05997 0.05458 -0.0129 0.0228 1.0000
8.750 0.8853 0.06439 0.05928 -0.0122 0.0223 1.0000
9.000 0.8763 0.06877 0.06389 -0.0118 0.0219 1.0000
9.250 0.8611 0.07303 0.06829 -0.0114 0.0221 1.0000
9.500 0.8435 0.07796 0.07333 -0.0129 0.0224 1.0000
9.750 0.8269 0.08386 0.07930 -0.0164 0.0230 1.0000
10.000 0.8128 0.09096 0.08644 -0.0216 0.0235 1.0000
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Polar data table (+)
Polar graphs
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