NLR-7223-43 AIRFOIL (nl722343-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: NLR-7223-43 AIRFOIL (nl722343-il) Reynolds number: 500,000 Max Cl/Cd: 67.38 at α=6.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-nl722343-il-500000-n5.txt Download as CSV file: xf-nl722343-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NLR-7223-43 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.000 -0.5328 0.07502 0.07269 -0.0338 1.0000 0.0080
-8.750 -0.5468 0.06958 0.06727 -0.0380 1.0000 0.0079
-8.500 -0.5679 0.06560 0.06328 -0.0388 1.0000 0.0079
-8.250 -0.5790 0.06178 0.05941 -0.0387 1.0000 0.0078
-8.000 -0.5888 0.05807 0.05562 -0.0378 1.0000 0.0077
-7.750 -0.5840 0.05288 0.05027 -0.0400 0.9979 0.0076
-7.500 -0.5692 0.04634 0.04345 -0.0438 0.9937 0.0075
-7.250 -0.5531 0.03998 0.03675 -0.0461 0.9890 0.0074
-7.000 -0.5348 0.03158 0.02776 -0.0480 0.9853 0.0075
-6.750 -0.5200 0.02388 0.01925 -0.0473 0.9789 0.0078
-6.500 -0.4946 0.02028 0.01504 -0.0475 0.9759 0.0081
-6.250 -0.4662 0.01839 0.01287 -0.0483 0.9740 0.0084
-6.000 -0.4393 0.01771 0.01213 -0.0486 0.9706 0.0088
-5.750 -0.4123 0.01667 0.01093 -0.0487 0.9671 0.0091
-5.500 -0.3834 0.01558 0.00967 -0.0492 0.9646 0.0093
-5.250 -0.3537 0.01442 0.00835 -0.0497 0.9626 0.0096
-5.000 -0.3232 0.01348 0.00729 -0.0504 0.9609 0.0099
-4.750 -0.2954 0.01273 0.00644 -0.0505 0.9577 0.0102
-4.500 -0.2681 0.01211 0.00576 -0.0504 0.9538 0.0106
-4.250 -0.2394 0.01147 0.00507 -0.0508 0.9508 0.0110
-4.000 -0.2093 0.01094 0.00452 -0.0514 0.9485 0.0116
-3.750 -0.1783 0.01053 0.00409 -0.0523 0.9465 0.0122
-3.500 -0.1504 0.01022 0.00376 -0.0523 0.9427 0.0131
-3.250 -0.1221 0.00990 0.00341 -0.0525 0.9388 0.0142
-3.000 -0.0920 0.00954 0.00305 -0.0530 0.9352 0.0154
-2.750 -0.0600 0.00926 0.00274 -0.0539 0.9310 0.0171
-2.500 -0.0330 0.00901 0.00248 -0.0536 0.9243 0.0204
-2.250 -0.0017 0.00873 0.00221 -0.0543 0.9167 0.0312
-2.000 0.0255 0.00836 0.00198 -0.0540 0.9009 0.0771
-1.750 0.0491 0.00781 0.00173 -0.0532 0.8768 0.1918
-1.500 0.0688 0.00657 0.00138 -0.0522 0.8532 0.4850
-1.250 0.0911 0.00641 0.00173 -0.0508 0.8369 0.6796
-1.000 0.1171 0.00660 0.00191 -0.0500 0.8234 0.7068
-0.750 0.1433 0.00674 0.00200 -0.0492 0.8086 0.7218
-0.500 0.1702 0.00678 0.00198 -0.0488 0.7913 0.7261
-0.250 0.1970 0.00683 0.00191 -0.0484 0.7675 0.7275
0.000 0.2227 0.00693 0.00183 -0.0478 0.7232 0.7279
0.250 0.2428 0.00735 0.00179 -0.0460 0.6227 0.7284
0.500 0.2646 0.00778 0.00185 -0.0448 0.5399 0.7291
0.750 0.2877 0.00817 0.00191 -0.0439 0.4666 0.7296
1.000 0.3118 0.00851 0.00198 -0.0433 0.4040 0.7300
1.250 0.3365 0.00882 0.00205 -0.0427 0.3493 0.7304
1.500 0.3616 0.00912 0.00213 -0.0423 0.3014 0.7308
1.750 0.3871 0.00939 0.00222 -0.0419 0.2609 0.7312
2.000 0.4130 0.00961 0.00231 -0.0416 0.2316 0.7316
2.250 0.4392 0.00981 0.00241 -0.0413 0.2112 0.7320
2.500 0.4656 0.00999 0.00251 -0.0411 0.1964 0.7324
2.750 0.4922 0.01016 0.00262 -0.0409 0.1852 0.7327
3.000 0.5187 0.01031 0.00275 -0.0406 0.1769 0.7332
3.500 0.5716 0.01063 0.00302 -0.0401 0.1618 0.7341
3.750 0.5978 0.01080 0.00318 -0.0399 0.1562 0.7347
4.000 0.6242 0.01096 0.00336 -0.0396 0.1516 0.7354
4.250 0.6507 0.01110 0.00352 -0.0394 0.1474 0.7360
4.500 0.6769 0.01128 0.00371 -0.0391 0.1428 0.7366
4.750 0.7027 0.01149 0.00392 -0.0388 0.1384 0.7372
5.000 0.7292 0.01163 0.00411 -0.0385 0.1338 0.7378
5.250 0.7551 0.01183 0.00429 -0.0382 0.1263 0.7384
5.500 0.7813 0.01200 0.00448 -0.0380 0.1187 0.7391
5.750 0.8070 0.01221 0.00470 -0.0377 0.1097 0.7399
6.000 0.8329 0.01242 0.00490 -0.0374 0.0987 0.7406
6.250 0.8578 0.01273 0.00514 -0.0370 0.0817 0.7414
6.500 0.8817 0.01317 0.00551 -0.0364 0.0652 0.7423
6.750 0.9057 0.01361 0.00591 -0.0359 0.0514 0.7432
7.000 0.9291 0.01413 0.00637 -0.0353 0.0377 0.7441
7.250 0.9524 0.01467 0.00687 -0.0346 0.0271 0.7451
7.500 0.9759 0.01518 0.00739 -0.0340 0.0218 0.7460
7.750 0.9992 0.01571 0.00794 -0.0333 0.0189 0.7471
8.000 1.0228 0.01617 0.00848 -0.0327 0.0174 0.7481
8.250 1.0460 0.01666 0.00906 -0.0320 0.0161 0.7492
8.500 1.0684 0.01725 0.00972 -0.0313 0.0149 0.7505
8.750 1.0903 0.01788 0.01044 -0.0304 0.0141 0.7518
9.000 1.1125 0.01844 0.01112 -0.0296 0.0134 0.7533
9.250 1.1341 0.01903 0.01180 -0.0288 0.0128 0.7550
9.500 1.1553 0.01966 0.01251 -0.0279 0.0121 0.7568
9.750 1.1752 0.02039 0.01333 -0.0269 0.0116 0.7588
10.000 1.1923 0.02140 0.01445 -0.0254 0.0110 0.7609
10.500 1.2290 0.02294 0.01625 -0.0229 0.0106 0.7656
10.750 1.2454 0.02382 0.01728 -0.0214 0.0103 0.7687
11.000 1.2608 0.02474 0.01834 -0.0198 0.0100 0.7724
11.250 1.2747 0.02573 0.01946 -0.0181 0.0098 0.7766
11.500 1.2875 0.02670 0.02059 -0.0161 0.0095 0.7820
11.750 1.2966 0.02771 0.02176 -0.0137 0.0093 0.7895
12.000 1.3036 0.02875 0.02296 -0.0110 0.0092 0.8006
12.250 1.3089 0.02978 0.02419 -0.0081 0.0090 0.8242
12.500 1.3171 0.03095 0.02573 -0.0063 0.0089 1.0000
12.750 1.3197 0.03241 0.02731 -0.0038 0.0088 1.0000
13.000 1.3199 0.03412 0.02914 -0.0014 0.0087 1.0000
13.250 1.3174 0.03612 0.03127 0.0008 0.0086 1.0000
13.500 1.3124 0.03849 0.03377 0.0027 0.0085 1.0000
13.750 1.3042 0.04137 0.03680 0.0041 0.0084 1.0000
14.000 1.2958 0.04458 0.04016 0.0047 0.0084 1.0000
14.250 1.2838 0.04857 0.04432 0.0044 0.0083 1.0000
14.500 1.2719 0.05317 0.04910 0.0030 0.0082 1.0000
14.750 1.2598 0.05855 0.05465 0.0002 0.0082 1.0000
15.000 1.2442 0.06534 0.06163 -0.0040 0.0082 1.0000
15.250 1.2267 0.07315 0.06961 -0.0091 0.0082 1.0000
15.500 1.2068 0.08160 0.07821 -0.0144 0.0082 1.0000
15.750 1.1868 0.09017 0.08691 -0.0196 0.0082 1.0000
16.000 1.1661 0.09889 0.09577 -0.0248 0.0082 1.0000
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Polar data table (+)
Polar graphs
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