NACA 747A315 (naca747a315-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: NACA 747A315 (naca747a315-il) Reynolds number: 500,000 Max Cl/Cd: 89.85 at α=7.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-naca747a315-il-500000.txt Download as CSV file: xf-naca747a315-il-500000.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 = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.750 -0.4743 0.09764 0.09547 -0.0343 0.9459 0.0318
-11.500 -0.6820 0.05505 0.05216 -0.0582 0.9053 0.0257
-11.250 -0.6961 0.05266 0.04959 -0.0558 0.8826 0.0258
-11.000 -0.6925 0.05089 0.04775 -0.0540 0.8656 0.0243
-10.750 -0.7170 0.04764 0.04425 -0.0500 0.8479 0.0241
-10.500 -0.7421 0.04441 0.04072 -0.0447 0.8327 0.0240
-10.250 -0.7601 0.04041 0.03633 -0.0402 0.8203 0.0239
-10.000 -0.7710 0.03623 0.03172 -0.0362 0.8092 0.0236
-9.750 -0.7742 0.03244 0.02745 -0.0326 0.7997 0.0236
-9.500 -0.7677 0.02955 0.02414 -0.0300 0.7902 0.0239
-9.250 -0.7551 0.02729 0.02152 -0.0280 0.7818 0.0241
-9.000 -0.7384 0.02556 0.01947 -0.0265 0.7733 0.0246
-8.750 -0.7195 0.02445 0.01807 -0.0252 0.7655 0.0250
-8.500 -0.6988 0.02253 0.01590 -0.0244 0.7577 0.0257
-8.250 -0.6757 0.02146 0.01475 -0.0240 0.7507 0.0263
-8.000 -0.6518 0.02057 0.01377 -0.0236 0.7432 0.0268
-7.750 -0.6278 0.01983 0.01292 -0.0230 0.7363 0.0274
-7.500 -0.6030 0.01906 0.01205 -0.0227 0.7295 0.0281
-7.250 -0.5780 0.01831 0.01118 -0.0223 0.7227 0.0288
-7.000 -0.5531 0.01774 0.01047 -0.0218 0.7165 0.0296
-6.750 -0.5281 0.01692 0.00957 -0.0214 0.7098 0.0305
-6.500 -0.5043 0.01615 0.00878 -0.0209 0.7036 0.0316
-6.250 -0.4798 0.01566 0.00826 -0.0205 0.6975 0.0326
-6.000 -0.4552 0.01518 0.00773 -0.0200 0.6910 0.0337
-5.750 -0.4308 0.01479 0.00725 -0.0194 0.6854 0.0350
-5.500 -0.4069 0.01425 0.00667 -0.0188 0.6796 0.0363
-5.250 -0.3839 0.01372 0.00614 -0.0181 0.6738 0.0383
-5.000 -0.3592 0.01345 0.00580 -0.0176 0.6686 0.0405
-4.750 -0.3335 0.01319 0.00551 -0.0173 0.6631 0.0426
-4.500 -0.3109 0.01264 0.00497 -0.0165 0.6577 0.0461
-4.250 -0.2856 0.01242 0.00468 -0.0160 0.6528 0.0497
-4.000 -0.2612 0.01204 0.00433 -0.0155 0.6479 0.0553
-3.750 -0.2358 0.01177 0.00405 -0.0151 0.6428 0.0624
-3.500 -0.2109 0.01148 0.00376 -0.0147 0.6382 0.0736
-3.250 -0.1871 0.01111 0.00351 -0.0141 0.6340 0.1019
-3.000 -0.1669 0.01037 0.00324 -0.0131 0.6295 0.2063
-2.750 -0.1514 0.00935 0.00293 -0.0114 0.6253 0.3814
-2.500 -0.1405 0.00817 0.00259 -0.0087 0.6215 0.5924
-2.250 -0.1230 0.00781 0.00280 -0.0063 0.6177 0.7520
-2.000 -0.0963 0.00791 0.00292 -0.0058 0.6136 0.7842
-1.750 -0.0690 0.00804 0.00303 -0.0054 0.6098 0.8017
-1.500 -0.0417 0.00820 0.00312 -0.0051 0.6064 0.8150
-1.250 -0.0140 0.00840 0.00328 -0.0048 0.6032 0.8244
-1.000 0.0132 0.00856 0.00342 -0.0044 0.6001 0.8349
-0.750 0.0389 0.00890 0.00378 -0.0034 0.5970 0.8501
-0.500 0.0638 0.00937 0.00428 -0.0019 0.5940 0.8649
-0.250 0.0903 0.00962 0.00453 -0.0009 0.5913 0.8716
0.000 0.1177 0.00976 0.00462 -0.0007 0.5887 0.8764
0.250 0.1451 0.00988 0.00466 -0.0007 0.5861 0.8811
0.500 0.1724 0.00988 0.00467 -0.0006 0.5838 0.8841
0.750 0.2002 0.00992 0.00471 -0.0005 0.5811 0.8865
1.000 0.2282 0.00996 0.00473 -0.0006 0.5785 0.8889
1.250 0.2563 0.00997 0.00473 -0.0008 0.5762 0.8910
1.500 0.2846 0.00998 0.00471 -0.0011 0.5742 0.8929
1.750 0.3129 0.01002 0.00471 -0.0014 0.5722 0.8950
2.000 0.3413 0.01011 0.00475 -0.0018 0.5701 0.8969
2.250 0.3696 0.01010 0.00476 -0.0022 0.5682 0.8988
2.500 0.3975 0.01008 0.00478 -0.0023 0.5660 0.9001
2.750 0.4255 0.01010 0.00482 -0.0026 0.5639 0.9014
3.000 0.4535 0.01012 0.00486 -0.0027 0.5614 0.9030
3.250 0.4817 0.01014 0.00487 -0.0030 0.5587 0.9046
3.500 0.5100 0.01019 0.00491 -0.0033 0.5562 0.9061
3.750 0.5384 0.01030 0.00501 -0.0036 0.5537 0.9077
4.000 0.5662 0.01031 0.00509 -0.0039 0.5514 0.9097
4.250 0.5942 0.01034 0.00516 -0.0042 0.5487 0.9117
4.500 0.6225 0.01034 0.00519 -0.0046 0.5450 0.9134
4.750 0.6506 0.01032 0.00515 -0.0048 0.5404 0.9148
5.000 0.6776 0.01033 0.00519 -0.0048 0.5355 0.9163
5.250 0.7043 0.01025 0.00518 -0.0048 0.5294 0.9179
5.500 0.7311 0.01023 0.00512 -0.0047 0.5213 0.9196
5.750 0.7568 0.01013 0.00511 -0.0044 0.5129 0.9219
6.000 0.7834 0.01017 0.00512 -0.0044 0.5061 0.9242
6.250 0.8095 0.01012 0.00518 -0.0043 0.4977 0.9265
6.500 0.8357 0.01015 0.00520 -0.0043 0.4887 0.9287
6.750 0.8609 0.01012 0.00524 -0.0040 0.4775 0.9308
7.000 0.8856 0.01013 0.00532 -0.0036 0.4647 0.9330
7.250 0.9090 0.01019 0.00540 -0.0031 0.4464 0.9356
7.500 0.9299 0.01035 0.00550 -0.0021 0.4098 0.9389
7.750 0.9353 0.01121 0.00597 0.0011 0.3337 0.9444
8.000 0.9365 0.01219 0.00667 0.0049 0.2718 0.9511
8.250 0.9344 0.01321 0.00742 0.0091 0.2177 0.9598
8.500 0.9344 0.01432 0.00833 0.0125 0.1723 0.9705
8.750 0.9455 0.01616 0.00986 0.0120 0.1140 0.9795
9.000 0.9614 0.01814 0.01159 0.0102 0.0701 0.9881
9.250 0.9734 0.01987 0.01318 0.0095 0.0484 1.0000
9.500 0.9745 0.02098 0.01427 0.0119 0.0426 1.0000
9.750 0.9796 0.02231 0.01559 0.0133 0.0381 1.0000
10.000 0.9871 0.02361 0.01691 0.0144 0.0352 1.0000
10.250 0.9910 0.02524 0.01855 0.0157 0.0328 1.0000
10.500 0.9996 0.02657 0.01993 0.0166 0.0306 1.0000
10.750 1.0063 0.02807 0.02146 0.0175 0.0291 1.0000
11.000 1.0052 0.03020 0.02360 0.0188 0.0275 1.0000
11.250 1.0149 0.03154 0.02500 0.0195 0.0266 1.0000
11.500 1.0233 0.03300 0.02651 0.0201 0.0255 1.0000
11.750 1.0295 0.03465 0.02820 0.0208 0.0244 1.0000
12.000 1.0334 0.03652 0.03009 0.0216 0.0236 1.0000
12.250 1.0348 0.03862 0.03222 0.0224 0.0231 1.0000
12.500 1.0392 0.04052 0.03418 0.0231 0.0226 1.0000
12.750 1.0478 0.04212 0.03584 0.0235 0.0221 1.0000
13.000 1.0561 0.04378 0.03756 0.0239 0.0215 1.0000
13.250 1.0635 0.04550 0.03934 0.0243 0.0211 1.0000
13.500 1.0714 0.04723 0.04111 0.0247 0.0205 1.0000
13.750 1.0793 0.04898 0.04290 0.0249 0.0200 1.0000
14.000 1.0872 0.05072 0.04467 0.0252 0.0197 1.0000
14.250 1.0948 0.05246 0.04643 0.0256 0.0193 1.0000
14.500 1.1035 0.05402 0.04800 0.0263 0.0190 1.0000
14.750 1.1122 0.05574 0.04981 0.0267 0.0186 1.0000
15.000 1.1203 0.05768 0.05185 0.0266 0.0182 1.0000
15.250 1.1293 0.05944 0.05369 0.0268 0.0180 1.0000
15.500 1.1379 0.06129 0.05562 0.0269 0.0177 1.0000
15.750 1.1455 0.06330 0.05773 0.0269 0.0175 1.0000
16.000 1.1529 0.06537 0.05990 0.0269 0.0172 1.0000
16.250 1.1593 0.06759 0.06220 0.0267 0.0169 1.0000
16.500 1.1653 0.06988 0.06458 0.0265 0.0167 1.0000
16.750 1.1700 0.07237 0.06717 0.0262 0.0166 1.0000
17.000 1.1734 0.07507 0.06997 0.0256 0.0164 1.0000
17.250 1.1759 0.07797 0.07296 0.0250 0.0162 1.0000
17.500 1.1780 0.08091 0.07600 0.0243 0.0160 1.0000
17.750 1.1789 0.08408 0.07928 0.0235 0.0159 1.0000
18.000 1.1772 0.08773 0.08308 0.0225 0.0159 1.0000
18.250 1.1770 0.09115 0.08658 0.0215 0.0157 1.0000
18.500 1.1739 0.09510 0.09065 0.0201 0.0156 1.0000
18.750 1.1667 0.09973 0.09543 0.0186 0.0155 1.0000
19.000 1.1564 0.10503 0.10090 0.0163 0.0155 1.0000
19.250 1.1454 0.11061 0.10664 0.0137 0.0155 1.0000
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