NACA 747A315 (naca747a315-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA 747A315 (naca747a315-il) Reynolds number: 200,000 Max Cl/Cd: 61.57 at α=7.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-naca747a315-il-200000-n5.txt Download as CSV file: xf-naca747a315-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NACA 747A315
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
------ -------- --------- --------- -------- -------- --------
-12.250 -0.5456 0.09086 0.08741 -0.0353 1.0000 0.0234
-12.000 -0.6036 0.07057 0.06701 -0.0500 1.0000 0.0229
-11.750 -0.6435 0.06119 0.05738 -0.0565 0.9478 0.0227
-11.500 -0.6735 0.05501 0.05087 -0.0583 0.9127 0.0226
-11.250 -0.7035 0.05042 0.04592 -0.0563 0.8876 0.0227
-11.000 -0.7252 0.04696 0.04214 -0.0530 0.8679 0.0227
-10.750 -0.7461 0.04362 0.03841 -0.0486 0.8512 0.0229
-10.500 -0.7611 0.04053 0.03487 -0.0441 0.8374 0.0231
-10.250 -0.7664 0.03753 0.03139 -0.0406 0.8254 0.0234
-10.000 -0.7650 0.03479 0.02814 -0.0377 0.8144 0.0237
-9.750 -0.7535 0.03311 0.02622 -0.0359 0.8047 0.0240
-9.500 -0.7375 0.03211 0.02512 -0.0346 0.7945 0.0245
-9.250 -0.7210 0.03110 0.02395 -0.0333 0.7854 0.0251
-9.000 -0.7038 0.02995 0.02260 -0.0321 0.7765 0.0258
-8.750 -0.6855 0.02862 0.02101 -0.0309 0.7688 0.0265
-8.500 -0.6655 0.02715 0.01924 -0.0299 0.7609 0.0271
-8.250 -0.6442 0.02580 0.01759 -0.0290 0.7540 0.0277
-8.000 -0.6211 0.02463 0.01615 -0.0284 0.7464 0.0283
-7.750 -0.5981 0.02362 0.01506 -0.0278 0.7396 0.0290
-7.500 -0.5747 0.02289 0.01428 -0.0274 0.7323 0.0298
-7.250 -0.5513 0.02223 0.01352 -0.0268 0.7254 0.0310
-7.000 -0.5272 0.02148 0.01263 -0.0263 0.7192 0.0321
-6.750 -0.5026 0.02071 0.01172 -0.0258 0.7123 0.0332
-6.500 -0.4789 0.01995 0.01087 -0.0252 0.7065 0.0342
-6.250 -0.4557 0.01930 0.01021 -0.0247 0.7008 0.0353
-6.000 -0.4321 0.01875 0.00962 -0.0241 0.6946 0.0368
-5.750 -0.4086 0.01827 0.00905 -0.0234 0.6893 0.0387
-5.500 -0.3854 0.01777 0.00849 -0.0228 0.6839 0.0409
-5.250 -0.3622 0.01730 0.00801 -0.0222 0.6782 0.0433
-5.000 -0.3388 0.01689 0.00753 -0.0215 0.6731 0.0461
-4.750 -0.3156 0.01646 0.00705 -0.0208 0.6684 0.0492
-4.500 -0.2917 0.01610 0.00669 -0.0203 0.6629 0.0539
-4.250 -0.2681 0.01573 0.00628 -0.0196 0.6579 0.0593
-3.750 -0.2202 0.01506 0.00560 -0.0185 0.6484 0.0778
-3.500 -0.1968 0.01467 0.00529 -0.0179 0.6436 0.0977
-3.250 -0.1749 0.01418 0.00498 -0.0170 0.6396 0.1440
-3.000 -0.1561 0.01347 0.00468 -0.0158 0.6360 0.2427
-2.750 -0.1413 0.01254 0.00439 -0.0140 0.6317 0.3897
-2.500 -0.1303 0.01151 0.00418 -0.0110 0.6278 0.5694
-2.250 -0.1088 0.01150 0.00483 -0.0085 0.6243 0.7359
-2.000 -0.0837 0.01171 0.00497 -0.0075 0.6212 0.7747
-1.750 -0.0585 0.01193 0.00515 -0.0066 0.6176 0.7990
-1.500 -0.0333 0.01249 0.00572 -0.0050 0.6139 0.8278
-1.250 -0.0081 0.01312 0.00633 -0.0031 0.6105 0.8513
-1.000 0.0214 0.01341 0.00655 -0.0028 0.6075 0.8595
-0.750 0.0491 0.01348 0.00651 -0.0027 0.6048 0.8641
-0.500 0.0722 0.01352 0.00648 -0.0018 0.6015 0.8716
-0.250 0.1031 0.01365 0.00658 -0.0022 0.5981 0.8750
0.000 0.1317 0.01370 0.00659 -0.0023 0.5950 0.8782
0.250 0.1583 0.01369 0.00652 -0.0023 0.5923 0.8811
0.500 0.1832 0.01366 0.00643 -0.0019 0.5900 0.8844
0.750 0.2069 0.01363 0.00631 -0.0014 0.5879 0.8878
1.000 0.2357 0.01366 0.00634 -0.0017 0.5854 0.8892
1.250 0.2640 0.01369 0.00638 -0.0020 0.5828 0.8909
1.500 0.2917 0.01373 0.00641 -0.0022 0.5802 0.8928
1.750 0.3190 0.01376 0.00644 -0.0023 0.5776 0.8950
2.000 0.3457 0.01378 0.00644 -0.0023 0.5751 0.8972
2.250 0.3717 0.01381 0.00644 -0.0022 0.5731 0.8997
2.500 0.3969 0.01385 0.00645 -0.0020 0.5714 0.9026
2.750 0.4233 0.01391 0.00655 -0.0020 0.5693 0.9045
3.000 0.4509 0.01398 0.00668 -0.0022 0.5666 0.9059
3.250 0.4785 0.01406 0.00681 -0.0025 0.5640 0.9076
3.500 0.5059 0.01414 0.00692 -0.0026 0.5615 0.9096
3.750 0.5331 0.01420 0.00701 -0.0027 0.5589 0.9117
4.000 0.5601 0.01425 0.00706 -0.0028 0.5563 0.9138
4.250 0.5862 0.01433 0.00717 -0.0027 0.5537 0.9160
4.500 0.6103 0.01442 0.00737 -0.0024 0.5503 0.9187
4.750 0.6367 0.01452 0.00754 -0.0025 0.5469 0.9207
5.000 0.6645 0.01460 0.00768 -0.0027 0.5436 0.9226
5.250 0.6926 0.01465 0.00778 -0.0029 0.5405 0.9245
5.500 0.7185 0.01471 0.00791 -0.0028 0.5351 0.9268
5.750 0.7435 0.01471 0.00800 -0.0026 0.5281 0.9294
6.000 0.7699 0.01467 0.00795 -0.0024 0.5220 0.9320
6.250 0.7917 0.01464 0.00805 -0.0016 0.5116 0.9352
6.500 0.8173 0.01456 0.00802 -0.0013 0.4982 0.9374
6.750 0.8422 0.01453 0.00806 -0.0010 0.4843 0.9400
7.000 0.8656 0.01455 0.00814 -0.0005 0.4681 0.9435
7.250 0.8858 0.01460 0.00823 0.0006 0.4462 0.9481
7.500 0.9081 0.01475 0.00839 0.0011 0.4110 0.9515
7.750 0.9199 0.01534 0.00863 0.0030 0.3447 0.9570
8.000 0.9237 0.01651 0.00948 0.0055 0.2832 0.9647
8.250 0.9265 0.01796 0.01066 0.0075 0.2292 0.9743
8.500 0.9335 0.01976 0.01222 0.0076 0.1784 0.9847
8.750 0.9400 0.02163 0.01388 0.0075 0.1366 1.0000
9.000 0.9300 0.02291 0.01505 0.0114 0.1158 1.0000
9.250 0.9272 0.02449 0.01650 0.0137 0.0945 1.0000
9.500 0.9276 0.02613 0.01804 0.0154 0.0770 1.0000
9.750 0.9300 0.02778 0.01961 0.0168 0.0627 1.0000
10.000 0.9344 0.02937 0.02116 0.0179 0.0526 1.0000
10.250 0.9387 0.03103 0.02278 0.0189 0.0451 1.0000
10.500 0.9452 0.03258 0.02435 0.0198 0.0410 1.0000
10.750 0.9506 0.03425 0.02603 0.0206 0.0376 1.0000
11.000 0.9572 0.03586 0.02769 0.0213 0.0349 1.0000
11.250 0.9616 0.03769 0.02953 0.0220 0.0328 1.0000
11.500 0.9679 0.03940 0.03130 0.0226 0.0314 1.0000
11.750 0.9745 0.04111 0.03309 0.0231 0.0299 1.0000
12.000 0.9804 0.04295 0.03498 0.0235 0.0283 1.0000
12.250 0.9839 0.04505 0.03710 0.0239 0.0272 1.0000
12.500 0.9889 0.04705 0.03917 0.0243 0.0265 1.0000
12.750 0.9956 0.04894 0.04114 0.0246 0.0254 1.0000
13.000 1.0018 0.05091 0.04318 0.0248 0.0247 1.0000
13.250 1.0082 0.05287 0.04521 0.0250 0.0241 1.0000
13.500 1.0143 0.05491 0.04730 0.0251 0.0234 1.0000
13.750 1.0205 0.05695 0.04938 0.0252 0.0228 1.0000
14.000 1.0251 0.05916 0.05158 0.0253 0.0221 1.0000
14.250 1.0334 0.06107 0.05361 0.0253 0.0216 1.0000
14.500 1.0412 0.06305 0.05570 0.0254 0.0209 1.0000
14.750 1.0488 0.06510 0.05784 0.0252 0.0204 1.0000
15.000 1.0558 0.06723 0.06006 0.0251 0.0199 1.0000
15.250 1.0627 0.06939 0.06230 0.0250 0.0195 1.0000
15.500 1.0692 0.07163 0.06460 0.0248 0.0191 1.0000
15.750 1.0755 0.07391 0.06695 0.0245 0.0188 1.0000
16.000 1.0819 0.07621 0.06930 0.0241 0.0185 1.0000
16.250 1.0888 0.07843 0.07157 0.0240 0.0183 1.0000
16.500 1.0934 0.08109 0.07436 0.0235 0.0180 1.0000
16.750 1.0968 0.08397 0.07740 0.0229 0.0179 1.0000
17.000 1.0981 0.08722 0.08082 0.0221 0.0177 1.0000
17.250 1.0979 0.09075 0.08453 0.0211 0.0175 1.0000
17.500 1.0954 0.09471 0.08869 0.0197 0.0173 1.0000
17.750 1.0914 0.09896 0.09312 0.0182 0.0171 1.0000
18.000 1.0861 0.10353 0.09788 0.0163 0.0170 1.0000
18.250 1.0793 0.10846 0.10300 0.0141 0.0170 1.0000
18.500 1.0692 0.11414 0.10889 0.0114 0.0168 1.0000
18.750 1.0570 0.12038 0.11533 0.0082 0.0167 1.0000
19.000 1.0426 0.12728 0.12244 0.0044 0.0167 1.0000
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