NACA 65(2)-215 (naca652215-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA 65(2)-215 (naca652215-il) Reynolds number: 50,000 Max Cl/Cd: 23.51 at α=7.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-naca652215-il-50000-n5.txt Download as CSV file: xf-naca652215-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NACA 65(2)-215
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.500 -0.5269 0.10736 0.09981 -0.0455 1.0000 0.0601
-12.250 -0.5436 0.09868 0.09116 -0.0507 1.0000 0.0591
-12.000 -0.5731 0.08938 0.08186 -0.0567 1.0000 0.0579
-11.750 -0.6072 0.08150 0.07390 -0.0613 1.0000 0.0570
-11.500 -0.6406 0.07532 0.06757 -0.0639 1.0000 0.0562
-11.250 -0.6700 0.07056 0.06264 -0.0645 1.0000 0.0557
-11.000 -0.6950 0.06684 0.05874 -0.0636 1.0000 0.0554
-10.750 -0.7156 0.06390 0.05562 -0.0614 1.0000 0.0553
-10.500 -0.7339 0.06144 0.05300 -0.0581 1.0000 0.0551
-10.250 -0.7453 0.05901 0.05041 -0.0551 1.0000 0.0553
-10.000 -0.7554 0.05683 0.04806 -0.0516 1.0000 0.0554
-9.750 -0.7635 0.05488 0.04597 -0.0480 1.0000 0.0558
-9.500 -0.7702 0.05317 0.04412 -0.0442 1.0000 0.0563
-9.250 -0.7758 0.05163 0.04246 -0.0404 1.0000 0.0570
-9.000 -0.7803 0.05014 0.04081 -0.0366 1.0000 0.0580
-8.500 -0.7830 0.04699 0.03721 -0.0297 1.0000 0.0602
-8.250 -0.7726 0.04504 0.03494 -0.0280 0.9979 0.0614
-8.000 -0.7427 0.04259 0.03204 -0.0294 0.9916 0.0629
-7.750 -0.7094 0.04052 0.02954 -0.0308 0.9860 0.0645
-7.500 -0.6747 0.03871 0.02776 -0.0325 0.9813 0.0678
-7.250 -0.6381 0.03734 0.02627 -0.0342 0.9764 0.0721
-7.000 -0.5955 0.03617 0.02484 -0.0360 0.9732 0.0763
-6.750 -0.5615 0.03508 0.02378 -0.0370 0.9680 0.0811
-6.500 -0.5292 0.03412 0.02268 -0.0382 0.9626 0.0890
-6.250 -0.5067 0.03304 0.02164 -0.0383 0.9552 0.0961
-6.000 -0.4818 0.03190 0.02045 -0.0390 0.9487 0.1072
-5.750 -0.4678 0.03074 0.01939 -0.0381 0.9398 0.1237
-5.500 -0.4508 0.02909 0.01808 -0.0383 0.9332 0.1625
-5.250 -0.4535 0.02718 0.01696 -0.0353 0.9229 0.2603
-5.000 -0.4376 0.02703 0.01845 -0.0313 0.9178 0.5352
-4.750 -0.4266 0.02756 0.01883 -0.0278 0.9089 0.5962
-4.500 -0.4005 0.02958 0.02078 -0.0241 0.9037 0.6621
-4.250 -0.3555 0.03284 0.02390 -0.0206 0.9016 0.7150
-4.000 -0.3363 0.03332 0.02418 -0.0182 0.8942 0.7309
-3.750 -0.2991 0.03358 0.02419 -0.0193 0.8900 0.7402
-3.500 -0.2674 0.03343 0.02380 -0.0203 0.8859 0.7500
-3.250 -0.2558 0.03335 0.02357 -0.0180 0.8777 0.7593
-3.000 -0.2277 0.03321 0.02324 -0.0185 0.8728 0.7667
-2.750 -0.1994 0.03306 0.02292 -0.0191 0.8684 0.7739
-2.500 -0.1915 0.03291 0.02267 -0.0164 0.8605 0.7819
-2.250 -0.1605 0.03279 0.02238 -0.0175 0.8562 0.7874
-2.000 -0.1529 0.03254 0.02203 -0.0150 0.8494 0.7959
-1.750 -0.1285 0.03255 0.02194 -0.0149 0.8439 0.8007
-1.500 -0.1025 0.03239 0.02166 -0.0153 0.8396 0.8068
-1.250 -0.0905 0.03229 0.02149 -0.0134 0.8334 0.8137
-1.000 -0.0706 0.03232 0.02145 -0.0127 0.8276 0.8191
-0.750 -0.0488 0.03217 0.02122 -0.0125 0.8232 0.8259
-0.500 -0.0284 0.03221 0.02120 -0.0119 0.8181 0.8313
-0.250 -0.0146 0.03229 0.02125 -0.0103 0.8117 0.8378
0.000 0.0075 0.03221 0.02112 -0.0101 0.8074 0.8445
0.250 0.0387 0.03228 0.02116 -0.0112 0.8039 0.8491
0.500 0.0382 0.03244 0.02132 -0.0074 0.7959 0.8579
0.750 0.0666 0.03253 0.02139 -0.0081 0.7919 0.8631
1.000 0.0999 0.03258 0.02144 -0.0096 0.7889 0.8684
1.250 0.0972 0.03288 0.02175 -0.0056 0.7806 0.8777
1.500 0.1253 0.03305 0.02193 -0.0063 0.7763 0.8836
1.750 0.1538 0.03311 0.02201 -0.0070 0.7731 0.8909
2.000 0.1622 0.03356 0.02252 -0.0050 0.7652 0.8990
2.250 0.1857 0.03375 0.02274 -0.0050 0.7604 0.9072
2.500 0.2250 0.03394 0.02301 -0.0076 0.7574 0.9123
2.750 0.2316 0.03445 0.02358 -0.0055 0.7492 0.9232
3.000 0.2660 0.03475 0.02397 -0.0076 0.7445 0.9298
3.250 0.3044 0.03490 0.02422 -0.0099 0.7410 0.9368
3.500 0.3213 0.03559 0.02503 -0.0100 0.7321 0.9467
3.750 0.3621 0.03584 0.02541 -0.0130 0.7274 0.9531
4.000 0.3925 0.03632 0.02605 -0.0147 0.7203 0.9619
4.250 0.4307 0.03673 0.02663 -0.0178 0.7132 0.9689
4.500 0.4796 0.03673 0.02684 -0.0215 0.7091 0.9743
4.750 0.5043 0.03749 0.02780 -0.0231 0.6980 0.9855
5.000 0.5572 0.03723 0.02779 -0.0271 0.6932 0.9904
5.250 0.5576 0.03782 0.02849 -0.0243 0.6805 1.0000
5.500 0.5448 0.03811 0.02879 -0.0186 0.6689 1.0000
5.750 0.5805 0.03755 0.02846 -0.0190 0.6619 1.0000
6.000 0.5797 0.03787 0.02884 -0.0152 0.6483 1.0000
6.250 0.5950 0.03786 0.02897 -0.0133 0.6346 1.0000
6.500 0.6216 0.03711 0.02841 -0.0119 0.6191 1.0000
6.750 0.6578 0.03453 0.02607 -0.0095 0.5930 1.0000
7.000 0.6821 0.03174 0.02338 -0.0053 0.5500 1.0000
7.250 0.6833 0.03185 0.02355 -0.0017 0.5079 1.0000
7.500 0.6949 0.03150 0.02322 0.0012 0.4424 1.0000
7.750 0.7173 0.03051 0.02081 0.0055 0.2611 1.0000
8.000 0.7077 0.03297 0.02260 0.0083 0.1867 1.0000
8.250 0.7041 0.03535 0.02452 0.0102 0.1440 1.0000
8.500 0.7057 0.03750 0.02638 0.0118 0.1203 1.0000
8.750 0.7119 0.03937 0.02811 0.0130 0.1049 1.0000
9.000 0.7206 0.04111 0.02972 0.0141 0.0950 1.0000
9.250 0.7351 0.04248 0.03119 0.0151 0.0872 1.0000
9.500 0.7507 0.04388 0.03254 0.0160 0.0804 1.0000
9.750 0.7732 0.04495 0.03373 0.0168 0.0746 1.0000
10.000 0.8059 0.04586 0.03456 0.0173 0.0699 1.0000
10.250 0.8431 0.04687 0.03586 0.0174 0.0650 1.0000
10.500 0.8757 0.04829 0.03739 0.0172 0.0610 1.0000
10.750 0.9205 0.05032 0.03942 0.0160 0.0585 1.0000
11.000 0.9428 0.05281 0.04234 0.0163 0.0570 1.0000
11.250 0.9555 0.05543 0.04534 0.0171 0.0553 1.0000
11.500 0.9631 0.05812 0.04834 0.0180 0.0538 1.0000
11.750 0.9676 0.06088 0.05136 0.0189 0.0525 1.0000
12.000 0.9694 0.06381 0.05453 0.0197 0.0516 1.0000
12.250 0.9674 0.06707 0.05804 0.0205 0.0511 1.0000
12.500 0.9605 0.07067 0.06191 0.0211 0.0508 1.0000
12.750 0.9496 0.07461 0.06611 0.0214 0.0506 1.0000
13.000 0.9330 0.07907 0.07084 0.0212 0.0506 1.0000
13.250 0.9108 0.08431 0.07635 0.0203 0.0508 1.0000
13.500 0.8821 0.09066 0.08297 0.0181 0.0512 1.0000
13.750 0.8477 0.09863 0.09117 0.0143 0.0517 1.0000
14.000 0.8082 0.10890 0.10163 0.0082 0.0526 1.0000
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