NACA 66-206 (naca66206-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA 66-206 (naca66206-il) Reynolds number: 100,000 Max Cl/Cd: 35.94 at α=2.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-naca66206-il-100000-n5.txt Download as CSV file: xf-naca66206-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NACA 66-206
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
------ -------- --------- --------- -------- -------- --------
-8.750 -0.4522 0.08939 0.08472 -0.0246 1.0000 0.0352
-8.500 -0.4555 0.08534 0.08071 -0.0272 1.0000 0.0352
-8.250 -0.4592 0.08127 0.07668 -0.0297 1.0000 0.0353
-8.000 -0.4650 0.07739 0.07282 -0.0320 1.0000 0.0353
-7.750 -0.4688 0.07346 0.06887 -0.0335 1.0000 0.0353
-7.500 -0.4704 0.06937 0.06473 -0.0347 1.0000 0.0354
-7.250 -0.4703 0.06522 0.06052 -0.0355 1.0000 0.0354
-7.000 -0.4719 0.05886 0.05422 -0.0358 1.0000 0.0359
-6.750 -0.4700 0.05378 0.04916 -0.0354 1.0000 0.0366
-6.500 -0.4674 0.04935 0.04472 -0.0349 1.0000 0.0372
-6.250 -0.4642 0.04531 0.04062 -0.0345 1.0000 0.0377
-6.000 -0.4599 0.04137 0.03659 -0.0340 1.0000 0.0383
-5.750 -0.4542 0.03758 0.03266 -0.0333 1.0000 0.0387
-5.250 -0.4501 0.04407 0.03800 -0.0324 1.0000 0.0206
-5.000 -0.4370 0.04051 0.03420 -0.0314 1.0000 0.0200
-4.750 -0.4216 0.03724 0.03062 -0.0302 1.0000 0.0195
-4.500 -0.4042 0.03411 0.02712 -0.0289 1.0000 0.0192
-4.250 -0.3851 0.03121 0.02382 -0.0276 1.0000 0.0190
-4.000 -0.3642 0.02852 0.02070 -0.0263 1.0000 0.0191
-3.750 -0.3417 0.02672 0.01843 -0.0249 1.0000 0.0211
-3.500 -0.3196 0.02414 0.01541 -0.0240 1.0000 0.0240
-3.250 -0.2961 0.02205 0.01298 -0.0230 1.0000 0.0249
-3.000 -0.2723 0.02031 0.01090 -0.0219 1.0000 0.0262
-2.750 -0.2487 0.01889 0.00929 -0.0209 1.0000 0.0290
-2.500 -0.2257 0.01830 0.00846 -0.0198 1.0000 0.0353
-2.250 -0.2031 0.01674 0.00690 -0.0189 1.0000 0.0377
-2.000 -0.1803 0.01590 0.00597 -0.0181 1.0000 0.0412
-1.750 -0.1503 0.01530 0.00516 -0.0188 0.9972 0.0480
-1.500 -0.1191 0.01464 0.00456 -0.0198 0.9940 0.0783
-1.250 -0.1150 0.01184 0.00480 -0.0139 0.9916 0.8625
-1.000 -0.0640 0.01172 0.00449 -0.0176 0.9924 1.0000
-0.750 -0.0314 0.01183 0.00436 -0.0192 0.9880 1.0000
-0.500 0.0002 0.01192 0.00428 -0.0205 0.9833 1.0000
-0.250 0.0328 0.01205 0.00424 -0.0221 0.9791 1.0000
0.000 0.0638 0.01217 0.00425 -0.0233 0.9743 1.0000
0.250 0.0959 0.01231 0.00432 -0.0247 0.9698 1.0000
0.500 0.1285 0.01246 0.00444 -0.0262 0.9657 1.0000
0.750 0.1585 0.01260 0.00457 -0.0272 0.9601 1.0000
1.000 0.1940 0.01276 0.00476 -0.0292 0.9558 1.0000
1.250 0.2242 0.01290 0.00495 -0.0301 0.9490 1.0000
1.500 0.2597 0.01304 0.00518 -0.0320 0.9438 1.0000
1.750 0.2915 0.01318 0.00544 -0.0331 0.9372 1.0000
2.000 0.3274 0.01329 0.00580 -0.0350 0.9311 1.0000
2.250 0.3776 0.01296 0.00574 -0.0385 0.9106 1.0000
2.500 0.4263 0.01186 0.00487 -0.0392 0.8445 1.0000
2.750 0.4418 0.01233 0.00376 -0.0328 0.4410 1.0000
3.000 0.4486 0.01522 0.00462 -0.0300 0.0653 1.0000
3.250 0.4711 0.01607 0.00562 -0.0290 0.0510 1.0000
3.500 0.4937 0.01693 0.00667 -0.0279 0.0451 1.0000
3.750 0.5145 0.01810 0.00791 -0.0267 0.0386 1.0000
4.000 0.5374 0.01915 0.00908 -0.0258 0.0324 1.0000
4.250 0.5607 0.02073 0.01072 -0.0248 0.0295 1.0000
4.500 0.5861 0.02322 0.01331 -0.0241 0.0275 1.0000
4.750 0.6128 0.02532 0.01574 -0.0233 0.0253 1.0000
5.000 0.6388 0.02708 0.01795 -0.0224 0.0212 1.0000
5.250 0.6635 0.02990 0.02137 -0.0211 0.0202 1.0000
5.500 0.6860 0.03308 0.02507 -0.0197 0.0196 1.0000
5.750 0.7063 0.03656 0.02907 -0.0181 0.0195 1.0000
6.000 0.7244 0.04021 0.03320 -0.0165 0.0193 1.0000
6.250 0.7399 0.04288 0.03613 -0.0157 0.0168 1.0000
6.750 0.7550 0.05209 0.04595 -0.0136 0.0145 1.0000
7.000 0.7648 0.05600 0.05020 -0.0124 0.0143 1.0000
7.250 0.7703 0.06075 0.05521 -0.0117 0.0147 1.0000
7.500 0.7801 0.06398 0.05869 -0.0108 0.0150 1.0000
7.750 0.7890 0.06760 0.06257 -0.0101 0.0157 1.0000
8.000 0.7872 0.07359 0.06888 -0.0106 0.0177 1.0000
8.250 0.7815 0.07868 0.07409 -0.0116 0.0186 1.0000
8.500 0.7715 0.08341 0.07887 -0.0129 0.0195 1.0000
8.750 0.7628 0.08842 0.08390 -0.0158 0.0200 1.0000
9.000 0.7561 0.09427 0.08973 -0.0206 0.0208 1.0000
9.250 0.7524 0.09988 0.09529 -0.0245 0.0216 1.0000
9.500 0.7504 0.10512 0.10050 -0.0275 0.0229 1.0000
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Polar data table (+)
Polar graphs
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