NACA 63-415 AIRFOIL (n63415-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA 63-415 AIRFOIL (n63415-il) Reynolds number: 200,000 Max Cl/Cd: 70.01 at α=6° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-n63415-il-200000-n5.txt Download as CSV file: xf-n63415-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NACA 63-415 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-14.500 -0.7116 0.07866 0.07427 -0.0592 1.0000 0.0221
-14.250 -0.7467 0.06920 0.06456 -0.0655 1.0000 0.0220
-14.000 -0.7709 0.06247 0.05760 -0.0695 1.0000 0.0220
-13.750 -0.7875 0.05734 0.05227 -0.0722 1.0000 0.0222
-13.500 -0.8014 0.05289 0.04762 -0.0742 1.0000 0.0224
-13.250 -0.8121 0.04910 0.04361 -0.0755 1.0000 0.0227
-13.000 -0.8204 0.04579 0.04008 -0.0762 1.0000 0.0231
-12.750 -0.8276 0.04277 0.03681 -0.0764 1.0000 0.0235
-12.500 -0.8329 0.04014 0.03393 -0.0761 1.0000 0.0240
-12.250 -0.8283 0.03842 0.03217 -0.0755 1.0000 0.0243
-12.000 -0.8237 0.03689 0.03060 -0.0747 1.0000 0.0247
-11.750 -0.8196 0.03555 0.02921 -0.0735 1.0000 0.0251
-11.500 -0.8171 0.03421 0.02779 -0.0719 1.0000 0.0255
-11.250 -0.8172 0.03301 0.02651 -0.0695 1.0000 0.0260
-11.000 -0.8204 0.03199 0.02541 -0.0662 1.0000 0.0264
-10.750 -0.8044 0.03056 0.02381 -0.0663 0.9913 0.0273
-10.500 -0.7763 0.02904 0.02202 -0.0683 0.9811 0.0285
-10.250 -0.7472 0.02768 0.02063 -0.0704 0.9718 0.0295
-10.000 -0.7183 0.02657 0.01947 -0.0721 0.9612 0.0306
-9.750 -0.6894 0.02545 0.01824 -0.0737 0.9510 0.0318
-9.500 -0.6597 0.02435 0.01698 -0.0752 0.9414 0.0332
-9.250 -0.6322 0.02331 0.01584 -0.0762 0.9306 0.0346
-9.000 -0.6068 0.02245 0.01495 -0.0769 0.9195 0.0361
-8.750 -0.5812 0.02168 0.01410 -0.0774 0.9092 0.0378
-8.500 -0.5582 0.02096 0.01328 -0.0772 0.8981 0.0394
-8.250 -0.5364 0.02024 0.01246 -0.0768 0.8877 0.0410
-8.000 -0.5150 0.01954 0.01172 -0.0763 0.8781 0.0428
-7.750 -0.4936 0.01898 0.01111 -0.0758 0.8680 0.0451
-7.500 -0.4709 0.01846 0.01047 -0.0753 0.8596 0.0474
-7.250 -0.4498 0.01783 0.00981 -0.0747 0.8502 0.0500
-7.000 -0.4267 0.01732 0.00924 -0.0743 0.8426 0.0530
-6.750 -0.4033 0.01688 0.00870 -0.0739 0.8339 0.0564
-6.500 -0.3800 0.01633 0.00812 -0.0735 0.8268 0.0608
-6.250 -0.3557 0.01591 0.00764 -0.0732 0.8186 0.0663
-6.000 -0.3314 0.01541 0.00713 -0.0730 0.8115 0.0743
-5.750 -0.3067 0.01494 0.00668 -0.0729 0.8042 0.0873
-5.500 -0.2820 0.01442 0.00623 -0.0728 0.7969 0.1103
-5.250 -0.2570 0.01388 0.00580 -0.0728 0.7905 0.1478
-5.000 -0.2323 0.01323 0.00538 -0.0729 0.7830 0.2017
-4.750 -0.2076 0.01251 0.00496 -0.0731 0.7767 0.2812
-4.500 -0.1820 0.01196 0.00473 -0.0732 0.7698 0.3617
-4.250 -0.1550 0.01171 0.00461 -0.0733 0.7631 0.4161
-4.000 -0.1273 0.01158 0.00451 -0.0733 0.7572 0.4540
-3.750 -0.0996 0.01151 0.00449 -0.0733 0.7501 0.4885
-3.500 -0.0718 0.01148 0.00447 -0.0732 0.7441 0.5164
-3.250 -0.0436 0.01148 0.00444 -0.0732 0.7379 0.5362
-3.000 -0.0155 0.01147 0.00441 -0.0732 0.7311 0.5508
-2.750 0.0127 0.01149 0.00437 -0.0731 0.7256 0.5651
-2.500 0.0409 0.01150 0.00437 -0.0731 0.7190 0.5776
-2.250 0.0695 0.01149 0.00429 -0.0732 0.7126 0.5871
-2.000 0.0978 0.01149 0.00424 -0.0732 0.7072 0.5942
-1.750 0.1263 0.01149 0.00421 -0.0734 0.7006 0.6021
-1.500 0.1547 0.01149 0.00417 -0.0734 0.6947 0.6092
-1.250 0.1831 0.01150 0.00414 -0.0735 0.6890 0.6162
-1.000 0.2118 0.01151 0.00411 -0.0737 0.6825 0.6235
-0.750 0.2400 0.01152 0.00411 -0.0736 0.6771 0.6293
-0.500 0.2686 0.01154 0.00410 -0.0738 0.6713 0.6361
-0.250 0.2970 0.01156 0.00412 -0.0739 0.6649 0.6425
0.000 0.3253 0.01159 0.00413 -0.0739 0.6596 0.6485
0.250 0.3539 0.01163 0.00415 -0.0741 0.6539 0.6554
0.500 0.3820 0.01167 0.00421 -0.0742 0.6478 0.6612
0.750 0.4103 0.01172 0.00424 -0.0742 0.6426 0.6678
1.000 0.4389 0.01177 0.00430 -0.0744 0.6367 0.6749
1.250 0.4666 0.01182 0.00440 -0.0743 0.6308 0.6804
1.500 0.4950 0.01189 0.00444 -0.0744 0.6257 0.6875
1.750 0.5230 0.01195 0.00456 -0.0745 0.6194 0.6942
2.000 0.5507 0.01202 0.00467 -0.0745 0.6134 0.7005
2.250 0.5793 0.01211 0.00472 -0.0746 0.6082 0.7080
2.500 0.6065 0.01218 0.00489 -0.0745 0.6014 0.7142
2.750 0.6343 0.01226 0.00500 -0.0745 0.5953 0.7215
3.000 0.6621 0.01236 0.00512 -0.0745 0.5892 0.7284
3.250 0.6892 0.01244 0.00529 -0.0743 0.5824 0.7353
3.500 0.7172 0.01255 0.00540 -0.0744 0.5765 0.7433
3.750 0.7437 0.01264 0.00560 -0.0741 0.5692 0.7497
4.000 0.7710 0.01275 0.00574 -0.0740 0.5620 0.7577
4.250 0.7971 0.01284 0.00592 -0.0737 0.5529 0.7647
4.500 0.8233 0.01294 0.00603 -0.0733 0.5425 0.7727
4.750 0.8488 0.01304 0.00621 -0.0729 0.5308 0.7802
5.000 0.8742 0.01315 0.00640 -0.0724 0.5195 0.7883
5.250 0.8992 0.01328 0.00657 -0.0718 0.5068 0.7965
5.500 0.9233 0.01342 0.00674 -0.0711 0.4919 0.8050
5.750 0.9463 0.01359 0.00693 -0.0702 0.4704 0.8137
6.000 0.9675 0.01382 0.00712 -0.0690 0.4421 0.8232
6.250 0.9873 0.01413 0.00736 -0.0677 0.4103 0.8325
6.750 1.0225 0.01502 0.00807 -0.0644 0.3395 0.8540
7.000 1.0350 0.01572 0.00859 -0.0620 0.2958 0.8661
7.250 1.0445 0.01653 0.00922 -0.0593 0.2516 0.8802
7.500 1.0515 0.01738 0.00990 -0.0561 0.2121 0.8980
7.750 1.0577 0.01818 0.01058 -0.0529 0.1795 0.9226
8.000 1.0654 0.01893 0.01124 -0.0502 0.1513 1.0000
8.250 1.0759 0.01996 0.01212 -0.0484 0.1249 1.0000
8.500 1.0858 0.02103 0.01308 -0.0467 0.1035 1.0000
8.750 1.0953 0.02216 0.01413 -0.0450 0.0863 1.0000
9.000 1.1049 0.02332 0.01523 -0.0435 0.0739 1.0000
9.250 1.1149 0.02450 0.01639 -0.0421 0.0649 1.0000
9.500 1.1246 0.02574 0.01763 -0.0408 0.0583 1.0000
9.750 1.1333 0.02710 0.01897 -0.0395 0.0530 1.0000
10.000 1.1435 0.02839 0.02032 -0.0384 0.0490 1.0000
10.250 1.1520 0.02985 0.02179 -0.0373 0.0456 1.0000
10.500 1.1607 0.03134 0.02332 -0.0364 0.0429 1.0000
10.750 1.1699 0.03283 0.02488 -0.0355 0.0404 1.0000
11.000 1.1771 0.03453 0.02661 -0.0347 0.0383 1.0000
11.250 1.1837 0.03634 0.02848 -0.0339 0.0367 1.0000
11.500 1.1919 0.03803 0.03027 -0.0333 0.0350 1.0000
11.750 1.1993 0.03986 0.03216 -0.0327 0.0334 1.0000
12.000 1.2048 0.04189 0.03424 -0.0322 0.0321 1.0000
12.250 1.2087 0.04413 0.03653 -0.0317 0.0310 1.0000
12.500 1.2157 0.04613 0.03864 -0.0313 0.0299 1.0000
12.750 1.2215 0.04828 0.04089 -0.0310 0.0289 1.0000
13.000 1.2267 0.05053 0.04322 -0.0308 0.0279 1.0000
13.250 1.2314 0.05290 0.04565 -0.0307 0.0271 1.0000
13.500 1.2346 0.05549 0.04828 -0.0307 0.0264 1.0000
13.750 1.2387 0.05804 0.05091 -0.0306 0.0257 1.0000
14.000 1.2444 0.06048 0.05348 -0.0307 0.0250 1.0000
14.250 1.2497 0.06304 0.05615 -0.0308 0.0242 1.0000
14.500 1.2544 0.06569 0.05891 -0.0311 0.0236 1.0000
14.750 1.2585 0.06847 0.06178 -0.0315 0.0229 1.0000
15.000 1.2619 0.07138 0.06476 -0.0321 0.0224 1.0000
15.250 1.2649 0.07439 0.06782 -0.0327 0.0219 1.0000
15.500 1.2678 0.07746 0.07097 -0.0333 0.0214 1.0000
15.750 1.2705 0.08070 0.07439 -0.0340 0.0209 1.0000
16.000 1.2727 0.08404 0.07788 -0.0348 0.0205 1.0000
16.250 1.2740 0.08757 0.08156 -0.0358 0.0201 1.0000
16.500 1.2745 0.09128 0.08542 -0.0370 0.0198 1.0000
16.750 1.2741 0.09520 0.08949 -0.0384 0.0194 1.0000
17.000 1.2731 0.09925 0.09368 -0.0399 0.0192 1.0000
17.250 1.2714 0.10349 0.09805 -0.0417 0.0189 1.0000
17.500 1.2692 0.10790 0.10259 -0.0436 0.0187 1.0000
17.750 1.2666 0.11244 0.10725 -0.0458 0.0185 1.0000
18.000 1.2634 0.11713 0.11207 -0.0481 0.0183 1.0000
18.250 1.2598 0.12197 0.11703 -0.0507 0.0182 1.0000
18.500 1.2559 0.12691 0.12209 -0.0533 0.0180 1.0000
18.750 1.2515 0.13202 0.12731 -0.0562 0.0179 1.0000
19.000 1.2429 0.13819 0.13364 -0.0600 0.0177 1.0000
19.250 1.2289 0.14583 0.14150 -0.0649 0.0177 1.0000
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Polar data table (+)
Polar graphs
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