BOEING 737 OUTBOARD AIRFOIL (b737d-il) Xfoil prediction polar at RE=200,000 Ncrit=9
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Airfoil: BOEING 737 OUTBOARD AIRFOIL (b737d-il) Reynolds number: 200,000 Max Cl/Cd: 68.71 at α=5.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-b737d-il-200000.txt Download as CSV file: xf-b737d-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: BOEING 737 OUTBOARD 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.500 -0.5376 0.09709 0.09363 -0.0285 1.0000 0.0319
-9.250 -0.5453 0.09304 0.08953 -0.0314 1.0000 0.0319
-9.000 -0.5537 0.08956 0.08600 -0.0326 1.0000 0.0320
-8.750 -0.5413 0.08169 0.07830 -0.0316 1.0000 0.0332
-8.500 -0.5429 0.07805 0.07466 -0.0323 1.0000 0.0337
-8.250 -0.5440 0.07443 0.07101 -0.0331 1.0000 0.0342
-8.000 -0.5433 0.07079 0.06733 -0.0339 1.0000 0.0349
-7.750 -0.5415 0.06721 0.06369 -0.0346 1.0000 0.0356
-7.500 -0.5383 0.06373 0.06012 -0.0349 1.0000 0.0367
-7.250 -0.5339 0.06041 0.05669 -0.0348 1.0000 0.0380
-7.000 -0.5296 0.05750 0.05363 -0.0338 1.0000 0.0397
-6.750 -0.5311 0.05775 0.05352 -0.0295 1.0000 0.0422
-6.500 -0.5433 0.05777 0.05336 -0.0239 1.0000 0.0426
-6.250 -0.5291 0.05087 0.04620 -0.0260 0.9954 0.0437
-6.000 -0.5041 0.04585 0.04125 -0.0289 0.9907 0.0455
-5.750 -0.4742 0.04253 0.03779 -0.0317 0.9857 0.0486
-5.500 -0.4380 0.04249 0.03691 -0.0329 0.9786 0.0562
-5.250 -0.4123 0.03629 0.03093 -0.0360 0.9744 0.0602
-4.750 -0.3476 0.03112 0.02522 -0.0398 0.9641 0.0749
-4.500 -0.3146 0.02908 0.02282 -0.0415 0.9589 0.0874
-4.250 -0.2839 0.02705 0.02060 -0.0429 0.9534 0.1019
-4.000 -0.2557 0.02503 0.01853 -0.0438 0.9465 0.1188
-3.750 -0.2040 0.02207 0.01446 -0.0415 0.9431 0.0434
-3.500 -0.1740 0.01978 0.01208 -0.0416 0.9364 0.0408
-3.250 -0.1430 0.01936 0.01145 -0.0418 0.9299 0.0428
-3.000 -0.1142 0.01773 0.00974 -0.0416 0.9235 0.0426
-2.750 -0.0876 0.01655 0.00853 -0.0410 0.9164 0.0430
-2.500 -0.0643 0.01516 0.00719 -0.0400 0.9099 0.0451
-2.250 -0.0408 0.01454 0.00659 -0.0392 0.9022 0.0506
-2.000 -0.0163 0.01404 0.00604 -0.0384 0.8958 0.0562
-1.750 0.0065 0.01341 0.00535 -0.0374 0.8879 0.0686
-1.500 0.0121 0.01076 0.00487 -0.0339 0.8804 0.6452
-1.250 0.0269 0.01064 0.00518 -0.0296 0.8727 0.7821
-1.000 0.0473 0.01074 0.00530 -0.0271 0.8658 0.8233
-0.750 0.0651 0.01089 0.00553 -0.0236 0.8580 0.8602
-0.500 0.0848 0.01101 0.00564 -0.0208 0.8507 0.8853
-0.250 0.1083 0.01106 0.00563 -0.0192 0.8433 0.9012
0.000 0.1343 0.01108 0.00559 -0.0186 0.8372 0.9135
0.250 0.1628 0.01109 0.00555 -0.0186 0.8299 0.9232
0.500 0.1934 0.01108 0.00547 -0.0189 0.8240 0.9325
0.750 0.2245 0.01111 0.00547 -0.0196 0.8162 0.9432
1.000 0.2601 0.01112 0.00543 -0.0212 0.8112 0.9519
1.250 0.2974 0.01116 0.00547 -0.0233 0.8034 0.9603
1.500 0.3342 0.01113 0.00539 -0.0251 0.7968 0.9696
1.750 0.3767 0.01109 0.00535 -0.0283 0.7869 0.9754
2.000 0.4155 0.01099 0.00522 -0.0306 0.7757 0.9838
2.250 0.4574 0.01083 0.00503 -0.0335 0.7634 0.9904
2.500 0.4988 0.01071 0.00488 -0.0364 0.7524 0.9978
2.750 0.5261 0.01064 0.00483 -0.0368 0.7410 1.0000
3.000 0.5472 0.01059 0.00481 -0.0358 0.7301 1.0000
3.250 0.5688 0.01055 0.00476 -0.0348 0.7191 1.0000
3.500 0.5909 0.01051 0.00472 -0.0337 0.7069 1.0000
3.750 0.6134 0.01049 0.00469 -0.0326 0.6930 1.0000
4.000 0.6362 0.01047 0.00473 -0.0316 0.6771 1.0000
4.250 0.6590 0.01046 0.00474 -0.0306 0.6578 1.0000
4.500 0.6820 0.01046 0.00471 -0.0295 0.6357 1.0000
4.750 0.7047 0.01049 0.00473 -0.0283 0.6060 1.0000
5.000 0.7268 0.01060 0.00479 -0.0271 0.5661 1.0000
5.250 0.7476 0.01088 0.00486 -0.0257 0.5088 1.0000
5.500 0.7664 0.01143 0.00509 -0.0241 0.4400 1.0000
5.750 0.7845 0.01216 0.00550 -0.0226 0.3751 1.0000
6.000 0.8020 0.01300 0.00602 -0.0212 0.3197 1.0000
6.250 0.8214 0.01374 0.00657 -0.0202 0.2779 1.0000
6.500 0.8427 0.01431 0.00702 -0.0194 0.2384 1.0000
6.750 0.8630 0.01497 0.00754 -0.0185 0.2048 1.0000
7.000 0.8833 0.01567 0.00815 -0.0177 0.1749 1.0000
7.250 0.9032 0.01642 0.00880 -0.0168 0.1425 1.0000
7.500 0.9203 0.01750 0.00960 -0.0155 0.0973 1.0000
7.750 0.9349 0.01890 0.01081 -0.0138 0.0687 1.0000
8.000 0.9500 0.02023 0.01211 -0.0122 0.0579 1.0000
8.250 0.9672 0.02132 0.01324 -0.0108 0.0510 1.0000
8.500 0.9829 0.02271 0.01468 -0.0093 0.0464 1.0000
8.750 1.0010 0.02389 0.01595 -0.0080 0.0430 1.0000
9.000 1.0181 0.02529 0.01735 -0.0068 0.0400 1.0000
9.250 1.0363 0.02730 0.01945 -0.0057 0.0373 1.0000
9.500 1.0561 0.02869 0.02102 -0.0047 0.0352 1.0000
9.750 1.0756 0.03043 0.02295 -0.0038 0.0334 1.0000
10.000 1.0931 0.03209 0.02473 -0.0028 0.0316 1.0000
10.250 1.1098 0.03538 0.02813 -0.0021 0.0294 1.0000
10.500 1.1207 0.03792 0.03103 -0.0004 0.0285 1.0000
10.750 1.1295 0.04039 0.03386 0.0015 0.0280 1.0000
11.000 1.1334 0.04330 0.03714 0.0038 0.0276 1.0000
11.250 1.1310 0.04641 0.04061 0.0064 0.0274 1.0000
11.500 1.1224 0.04964 0.04415 0.0094 0.0273 1.0000
11.750 1.1100 0.05309 0.04790 0.0119 0.0274 1.0000
12.000 1.0949 0.05684 0.05193 0.0136 0.0274 1.0000
12.250 1.0776 0.06098 0.05632 0.0145 0.0275 1.0000
12.500 1.0583 0.06562 0.06118 0.0144 0.0276 1.0000
12.750 1.0375 0.07083 0.06661 0.0133 0.0278 1.0000
13.000 1.0154 0.07670 0.07266 0.0112 0.0280 1.0000
13.250 0.9922 0.08341 0.07953 0.0081 0.0283 1.0000
13.500 0.9683 0.09106 0.08731 0.0041 0.0287 1.0000
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Polar data table (+)
Polar graphs
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