NACA 65-209 (naca65209-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
|---|---|
|
Airfoil: NACA 65-209 (naca65209-il) Reynolds number: 100,000 Max Cl/Cd: 42.12 at α=3.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-naca65209-il-100000-n5.txt Download as CSV file: xf-naca65209-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NACA 65-209
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
------ -------- --------- --------- -------- -------- --------
-9.250 -0.5416 0.08511 0.08016 -0.0318 1.0000 0.0258
-9.000 -0.5451 0.08014 0.07523 -0.0347 1.0000 0.0253
-8.750 -0.5526 0.07528 0.07038 -0.0379 1.0000 0.0250
-8.500 -0.5625 0.07118 0.06627 -0.0395 1.0000 0.0247
-8.250 -0.5699 0.06702 0.06206 -0.0406 1.0000 0.0243
-8.000 -0.5751 0.06273 0.05765 -0.0413 1.0000 0.0244
-7.750 -0.5773 0.05861 0.05334 -0.0414 1.0000 0.0247
-7.500 -0.5765 0.05471 0.04921 -0.0409 1.0000 0.0251
-7.250 -0.5725 0.05120 0.04539 -0.0398 1.0000 0.0258
-7.000 -0.5668 0.04805 0.04190 -0.0382 1.0000 0.0263
-6.750 -0.5606 0.04461 0.03817 -0.0366 1.0000 0.0262
-6.500 -0.5528 0.04129 0.03448 -0.0347 1.0000 0.0262
-6.250 -0.5432 0.03833 0.03116 -0.0328 1.0000 0.0263
-6.000 -0.5317 0.03572 0.02814 -0.0307 1.0000 0.0265
-5.750 -0.5191 0.03301 0.02506 -0.0288 1.0000 0.0268
-5.500 -0.5069 0.02996 0.02177 -0.0274 1.0000 0.0287
-5.250 -0.4912 0.02855 0.02022 -0.0260 1.0000 0.0311
-5.000 -0.4665 0.02654 0.01785 -0.0258 0.9978 0.0324
-4.750 -0.4330 0.02443 0.01536 -0.0270 0.9930 0.0335
-4.500 -0.3995 0.02268 0.01328 -0.0281 0.9882 0.0351
-4.250 -0.3656 0.02164 0.01196 -0.0293 0.9831 0.0385
-4.000 -0.3340 0.01997 0.01028 -0.0304 0.9782 0.0412
-3.750 -0.3025 0.01883 0.00913 -0.0315 0.9728 0.0437
-3.500 -0.2703 0.01795 0.00816 -0.0327 0.9672 0.0471
-3.250 -0.2377 0.01721 0.00729 -0.0341 0.9616 0.0540
-3.000 -0.2053 0.01658 0.00657 -0.0354 0.9556 0.0644
-2.750 -0.1701 0.01577 0.00585 -0.0372 0.9514 0.0924
-2.500 -0.1577 0.01318 0.00582 -0.0353 0.9432 0.6348
-2.250 -0.1329 0.01327 0.00615 -0.0332 0.9378 0.7508
-2.000 -0.1151 0.01353 0.00648 -0.0295 0.9291 0.8097
-1.750 -0.0914 0.01379 0.00671 -0.0270 0.9239 0.8499
-1.500 -0.0649 0.01378 0.00657 -0.0266 0.9159 0.8614
-1.250 -0.0314 0.01372 0.00635 -0.0278 0.9109 0.8704
-1.000 -0.0034 0.01369 0.00623 -0.0279 0.9033 0.8798
-0.750 0.0291 0.01365 0.00609 -0.0289 0.8979 0.8879
-0.500 0.0577 0.01363 0.00601 -0.0291 0.8908 0.8976
-0.250 0.0895 0.01359 0.00591 -0.0300 0.8849 0.9062
0.000 0.1208 0.01357 0.00586 -0.0308 0.8788 0.9150
0.250 0.1510 0.01356 0.00582 -0.0314 0.8721 0.9251
0.500 0.1867 0.01352 0.00579 -0.0330 0.8672 0.9328
0.750 0.2182 0.01353 0.00582 -0.0340 0.8598 0.9424
1.000 0.2542 0.01350 0.00581 -0.0358 0.8548 0.9510
1.250 0.2897 0.01352 0.00592 -0.0377 0.8476 0.9594
1.500 0.3271 0.01351 0.00597 -0.0398 0.8419 0.9675
1.750 0.3637 0.01354 0.00609 -0.0419 0.8349 0.9764
2.000 0.4022 0.01354 0.00620 -0.0444 0.8284 0.9845
2.250 0.4399 0.01356 0.00640 -0.0467 0.8209 0.9937
2.500 0.4696 0.01359 0.00655 -0.0473 0.8129 1.0000
2.750 0.4886 0.01358 0.00664 -0.0454 0.7992 1.0000
3.000 0.5070 0.01323 0.00630 -0.0424 0.7696 1.0000
3.250 0.5213 0.01280 0.00576 -0.0380 0.7067 1.0000
3.500 0.5370 0.01275 0.00538 -0.0345 0.6125 1.0000
3.750 0.5455 0.01382 0.00526 -0.0304 0.3690 1.0000
4.000 0.5495 0.01639 0.00624 -0.0275 0.0936 1.0000
4.250 0.5692 0.01740 0.00705 -0.0264 0.0625 1.0000
4.500 0.5903 0.01825 0.00799 -0.0254 0.0543 1.0000
4.750 0.6115 0.01909 0.00889 -0.0244 0.0477 1.0000
5.000 0.6321 0.02006 0.00992 -0.0234 0.0425 1.0000
5.250 0.6531 0.02108 0.01104 -0.0224 0.0398 1.0000
5.500 0.6749 0.02228 0.01229 -0.0215 0.0377 1.0000
5.750 0.6982 0.02365 0.01370 -0.0208 0.0360 1.0000
6.000 0.7229 0.02533 0.01547 -0.0204 0.0346 1.0000
6.250 0.7485 0.02770 0.01793 -0.0202 0.0326 1.0000
6.500 0.7735 0.02900 0.01956 -0.0196 0.0304 1.0000
6.750 0.7982 0.03120 0.02210 -0.0189 0.0294 1.0000
7.000 0.8208 0.03373 0.02504 -0.0180 0.0286 1.0000
7.250 0.8408 0.03658 0.02834 -0.0168 0.0281 1.0000
7.500 0.8580 0.03954 0.03176 -0.0154 0.0272 1.0000
7.750 0.8733 0.04199 0.03459 -0.0143 0.0253 1.0000
8.000 0.8873 0.04428 0.03708 -0.0134 0.0238 1.0000
8.250 0.8968 0.04765 0.04079 -0.0120 0.0232 1.0000
8.500 0.9028 0.05139 0.04490 -0.0104 0.0230 1.0000
8.750 0.9052 0.05529 0.04917 -0.0087 0.0229 1.0000
9.000 0.9036 0.05934 0.05354 -0.0070 0.0229 1.0000
9.250 0.8978 0.06341 0.05793 -0.0053 0.0231 1.0000
9.500 0.8838 0.06768 0.06249 -0.0034 0.0234 1.0000
9.750 0.8616 0.07223 0.06728 -0.0020 0.0239 1.0000
10.000 0.8388 0.07750 0.07272 -0.0028 0.0244 1.0000
10.250 0.8169 0.08381 0.07915 -0.0060 0.0249 1.0000
10.500 0.7963 0.09184 0.08725 -0.0116 0.0255 1.0000
|
Polar data table (+)
Polar graphs
<< Back to NACA 65-209 (naca65209-il)