NLR-7223-62 AIRFOIL (nl722362-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: NLR-7223-62 AIRFOIL (nl722362-il) Reynolds number: 200,000 Max Cl/Cd: 52.92 at α=7° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-nl722362-il-200000-n5.txt Download as CSV file: xf-nl722362-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NLR-7223-62 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
------ -------- --------- --------- -------- -------- --------
-9.250 -0.4891 0.08907 0.08545 -0.0295 1.0000 0.0239
-9.000 -0.4919 0.08498 0.08141 -0.0315 1.0000 0.0230
-8.750 -0.4995 0.08019 0.07668 -0.0348 1.0000 0.0239
-8.500 -0.5108 0.07578 0.07231 -0.0376 1.0000 0.0230
-8.250 -0.5284 0.07257 0.06913 -0.0367 1.0000 0.0233
-8.000 -0.5483 0.06992 0.06649 -0.0337 1.0000 0.0229
-7.500 -0.5564 0.05570 0.05179 -0.0372 0.9877 0.0158
-7.000 -0.5379 0.04494 0.04027 -0.0376 0.9769 0.0162
-6.750 -0.5218 0.04174 0.03688 -0.0378 0.9741 0.0159
-6.500 -0.5094 0.03866 0.03354 -0.0366 0.9698 0.0156
-6.250 -0.4954 0.03532 0.02985 -0.0352 0.9659 0.0153
-6.000 -0.4783 0.03187 0.02598 -0.0339 0.9630 0.0151
-5.750 -0.4579 0.02875 0.02241 -0.0329 0.9609 0.0149
-5.500 -0.4349 0.02596 0.01915 -0.0320 0.9592 0.0150
-5.250 -0.4179 0.02397 0.01679 -0.0298 0.9554 0.0152
-5.000 -0.3959 0.02223 0.01467 -0.0285 0.9530 0.0154
-4.750 -0.3711 0.02086 0.01294 -0.0276 0.9512 0.0164
-4.500 -0.3461 0.01988 0.01191 -0.0274 0.9496 0.0175
-4.250 -0.3196 0.01885 0.01075 -0.0271 0.9484 0.0181
-4.000 -0.2927 0.01783 0.00961 -0.0269 0.9472 0.0186
-3.750 -0.2660 0.01697 0.00866 -0.0266 0.9461 0.0193
-3.500 -0.2394 0.01625 0.00788 -0.0264 0.9451 0.0200
-3.250 -0.2169 0.01565 0.00723 -0.0253 0.9429 0.0208
-3.000 -0.1993 0.01524 0.00682 -0.0234 0.9400 0.0223
-2.750 -0.1777 0.01493 0.00649 -0.0222 0.9378 0.0247
-2.500 -0.1543 0.01455 0.00608 -0.0213 0.9357 0.0277
-2.250 -0.1282 0.01424 0.00572 -0.0210 0.9338 0.0317
-2.000 -0.0999 0.01381 0.00534 -0.0211 0.9319 0.0459
-1.750 -0.0733 0.01287 0.00501 -0.0213 0.9298 0.1874
-1.500 -0.0052 0.01053 0.00541 -0.0296 0.9345 0.8661
-1.250 0.0674 0.01120 0.00602 -0.0374 0.9362 0.9514
-1.000 0.1201 0.01089 0.00557 -0.0420 0.9276 0.9570
-0.750 0.1589 0.01056 0.00510 -0.0431 0.9065 0.9643
-0.500 0.1964 0.01031 0.00471 -0.0443 0.8862 0.9706
-0.250 0.2289 0.01024 0.00457 -0.0450 0.8737 0.9772
0.000 0.2642 0.01013 0.00441 -0.0465 0.8641 0.9825
0.250 0.2984 0.01002 0.00424 -0.0478 0.8542 0.9874
0.500 0.3333 0.00986 0.00407 -0.0493 0.8413 0.9918
0.750 0.3671 0.00971 0.00388 -0.0505 0.8253 0.9960
1.000 0.4012 0.00954 0.00369 -0.0518 0.8027 1.0000
1.250 0.4215 0.00948 0.00361 -0.0501 0.7566 1.0000
1.500 0.4362 0.00973 0.00304 -0.0464 0.5998 1.0000
1.750 0.4515 0.01033 0.00311 -0.0438 0.4951 1.0000
2.000 0.4686 0.01088 0.00325 -0.0419 0.4109 1.0000
2.250 0.4872 0.01136 0.00340 -0.0403 0.3434 1.0000
2.500 0.5071 0.01176 0.00357 -0.0389 0.2952 1.0000
2.750 0.5279 0.01210 0.00373 -0.0377 0.2619 1.0000
3.000 0.5493 0.01239 0.00391 -0.0366 0.2398 1.0000
3.250 0.5709 0.01267 0.00411 -0.0354 0.2238 1.0000
3.500 0.5925 0.01295 0.00435 -0.0343 0.2117 1.0000
3.750 0.6144 0.01322 0.00458 -0.0332 0.2010 1.0000
4.000 0.6361 0.01349 0.00483 -0.0321 0.1927 1.0000
4.250 0.6578 0.01377 0.00508 -0.0310 0.1850 1.0000
4.500 0.6796 0.01405 0.00539 -0.0299 0.1784 1.0000
4.750 0.7014 0.01433 0.00568 -0.0288 0.1722 1.0000
5.000 0.7225 0.01468 0.00600 -0.0276 0.1667 1.0000
5.250 0.7447 0.01493 0.00633 -0.0266 0.1609 1.0000
5.500 0.7660 0.01526 0.00668 -0.0254 0.1548 1.0000
5.750 0.7874 0.01558 0.00705 -0.0243 0.1495 1.0000
6.000 0.8091 0.01584 0.00737 -0.0232 0.1417 1.0000
6.250 0.8306 0.01609 0.00768 -0.0221 0.1316 1.0000
6.500 0.8520 0.01635 0.00796 -0.0210 0.1200 1.0000
6.750 0.8735 0.01662 0.00827 -0.0199 0.1086 1.0000
7.000 0.8948 0.01691 0.00861 -0.0187 0.0933 1.0000
7.250 0.9146 0.01736 0.00899 -0.0175 0.0766 1.0000
7.500 0.9332 0.01800 0.00957 -0.0160 0.0597 1.0000
7.750 0.9506 0.01878 0.01030 -0.0143 0.0455 1.0000
8.000 0.9680 0.01958 0.01111 -0.0126 0.0368 1.0000
8.250 0.9847 0.02039 0.01197 -0.0108 0.0312 1.0000
8.500 1.0015 0.02115 0.01282 -0.0090 0.0276 1.0000
8.750 1.0168 0.02201 0.01374 -0.0070 0.0251 1.0000
9.000 1.0312 0.02288 0.01473 -0.0049 0.0236 1.0000
9.250 1.0450 0.02374 0.01574 -0.0027 0.0223 1.0000
9.500 1.0576 0.02466 0.01677 -0.0003 0.0212 1.0000
9.750 1.0682 0.02567 0.01788 0.0023 0.0204 1.0000
10.000 1.0755 0.02689 0.01917 0.0053 0.0197 1.0000
10.250 1.0849 0.02793 0.02035 0.0080 0.0191 1.0000
10.500 1.0933 0.02903 0.02162 0.0109 0.0185 1.0000
10.750 1.0991 0.03012 0.02286 0.0141 0.0177 1.0000
11.000 1.1021 0.03123 0.02409 0.0176 0.0172 1.0000
11.250 1.1045 0.03240 0.02538 0.0210 0.0167 1.0000
11.500 1.1059 0.03373 0.02682 0.0243 0.0163 1.0000
11.750 1.1065 0.03523 0.02843 0.0273 0.0160 1.0000
12.000 1.1060 0.03691 0.03021 0.0301 0.0158 1.0000
12.250 1.1050 0.03876 0.03220 0.0327 0.0156 1.0000
12.500 1.1009 0.04105 0.03462 0.0351 0.0153 1.0000
12.750 1.0973 0.04327 0.03706 0.0371 0.0152 1.0000
13.000 1.0927 0.04573 0.03970 0.0388 0.0151 1.0000
13.250 1.0845 0.04865 0.04286 0.0400 0.0150 1.0000
13.500 1.0743 0.05207 0.04648 0.0405 0.0149 1.0000
13.750 1.0632 0.05592 0.05054 0.0401 0.0148 1.0000
14.000 1.0500 0.06056 0.05537 0.0386 0.0148 1.0000
14.250 1.0329 0.06646 0.06150 0.0355 0.0147 1.0000
14.500 1.0168 0.07289 0.06812 0.0317 0.0147 1.0000
14.750 0.9991 0.08015 0.07555 0.0271 0.0148 1.0000
15.000 0.9786 0.08840 0.08397 0.0219 0.0149 1.0000
15.250 0.9563 0.09731 0.09301 0.0165 0.0150 1.0000
15.500 0.9322 0.10680 0.10263 0.0110 0.0150 1.0000
15.750 0.9114 0.11557 0.11147 0.0063 0.0152 1.0000
16.000 0.8790 0.12785 0.12385 -0.0005 0.0153 1.0000
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Polar data table (+)
Polar graphs
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