BOEING 707 .19 SPAN AIRFOIL (b707b-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: BOEING 707 .19 SPAN AIRFOIL (b707b-il) Reynolds number: 1,000,000 Max Cl/Cd: 67.02 at α=8.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-b707b-il-1000000.txt Download as CSV file: xf-b707b-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: BOEING 707 .19 SPAN AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-18.750 -1.2134 0.09052 0.08786 -0.0094 1.0000 0.0057
-18.500 -1.2439 0.08131 0.07846 -0.0146 1.0000 0.0056
-18.250 -1.2616 0.07459 0.07159 -0.0183 1.0000 0.0056
-18.000 -1.2765 0.06863 0.06550 -0.0213 1.0000 0.0057
-17.750 -1.2886 0.06348 0.06019 -0.0236 1.0000 0.0056
-17.500 -1.2962 0.05918 0.05578 -0.0253 1.0000 0.0057
-17.250 -1.3015 0.05541 0.05192 -0.0266 1.0000 0.0058
-17.000 -1.2958 0.05316 0.04964 -0.0272 1.0000 0.0060
-16.750 -1.2878 0.05126 0.04773 -0.0277 1.0000 0.0061
-16.500 -1.2828 0.04908 0.04551 -0.0281 1.0000 0.0062
-15.500 -1.2177 0.04613 0.04270 -0.0285 1.0000 0.0092
-15.250 -1.2134 0.04418 0.04071 -0.0285 1.0000 0.0090
-15.000 -1.2304 0.03983 0.03605 -0.0278 1.0000 0.0097
-14.750 -1.2355 0.03695 0.03297 -0.0268 1.0000 0.0101
-14.500 -1.2355 0.03468 0.03053 -0.0257 1.0000 0.0104
-14.250 -1.2033 0.03257 0.02816 -0.0304 0.9053 0.0106
-14.000 -1.1988 0.03239 0.02736 -0.0276 0.7282 0.0108
-13.000 -1.1494 0.03076 0.02555 -0.0226 0.6797 0.0116
-12.750 -1.1389 0.03025 0.02499 -0.0210 0.6749 0.0119
-12.500 -1.1283 0.02981 0.02449 -0.0192 0.6698 0.0122
-12.250 -1.1159 0.02977 0.02442 -0.0173 0.6664 0.0127
-12.000 -1.1070 0.02901 0.02357 -0.0151 0.6629 0.0129
-11.750 -1.0956 0.02933 0.02383 -0.0127 0.6605 0.0135
-11.500 -1.0870 0.02900 0.02341 -0.0099 0.6578 0.0136
-11.250 -1.0820 0.02976 0.02409 -0.0059 0.6555 0.0139
-11.000 -1.0727 0.02771 0.02184 -0.0039 0.6535 0.0142
-10.750 -1.0571 0.02636 0.02050 -0.0028 0.6519 0.0148
-10.500 -1.0388 0.02645 0.02070 -0.0016 0.6505 0.0156
-10.250 -1.0219 0.02584 0.02003 -0.0001 0.6490 0.0159
-10.000 -1.0042 0.02574 0.01987 0.0014 0.6471 0.0166
-9.750 -0.9863 0.02569 0.01973 0.0030 0.6447 0.0171
-9.250 -0.9514 0.02310 0.01687 0.0054 0.6417 0.0185
-9.000 -0.9300 0.02248 0.01628 0.0061 0.6404 0.0191
-8.750 -0.9088 0.02216 0.01595 0.0070 0.6390 0.0200
-8.500 -0.8907 0.02453 0.01825 0.0091 0.6375 0.0216
-8.250 -0.8691 0.02238 0.01594 0.0097 0.6365 0.0218
-8.000 -0.8458 0.02146 0.01494 0.0104 0.6358 0.0218
-7.750 -0.8214 0.01990 0.01329 0.0107 0.6350 0.0220
-7.500 -0.7973 0.01917 0.01251 0.0112 0.6341 0.0220
-7.250 -0.7729 0.01852 0.01181 0.0118 0.6332 0.0220
-7.000 -0.7485 0.01779 0.01104 0.0123 0.6321 0.0220
-6.750 -0.7241 0.01715 0.01036 0.0129 0.6307 0.0220
-6.500 -0.6998 0.01657 0.00975 0.0135 0.6292 0.0219
-6.250 -0.6760 0.01585 0.00900 0.0141 0.6275 0.0220
-6.000 -0.6549 0.01482 0.00796 0.0152 0.6263 0.0226
-5.750 -0.6325 0.01425 0.00738 0.0161 0.6251 0.0230
-5.500 -0.6094 0.01379 0.00689 0.0170 0.6239 0.0230
-5.250 -0.5850 0.01348 0.00652 0.0177 0.6225 0.0225
-5.000 -0.5602 0.01323 0.00623 0.0184 0.6210 0.0222
-4.750 -0.5351 0.01295 0.00596 0.0189 0.6200 0.0220
-4.500 -0.5099 0.01266 0.00566 0.0195 0.6171 0.0218
-4.250 -0.4860 0.01226 0.00526 0.0203 0.6143 0.0216
-4.000 -0.4633 0.01177 0.00474 0.0213 0.6126 0.0214
-3.750 -0.4394 0.01139 0.00433 0.0221 0.6093 0.0213
-3.500 -0.4149 0.01108 0.00397 0.0228 0.6045 0.0211
-3.250 -0.3896 0.01076 0.00365 0.0234 0.6005 0.0210
-3.000 -0.3640 0.01048 0.00335 0.0239 0.5961 0.0209
-2.750 -0.3381 0.01025 0.00309 0.0244 0.5921 0.0209
-2.500 -0.3119 0.01004 0.00286 0.0248 0.5880 0.0209
-2.250 -0.2853 0.00983 0.00265 0.0252 0.5832 0.0209
-2.000 -0.2587 0.00965 0.00245 0.0255 0.5774 0.0211
-1.750 -0.2318 0.00949 0.00227 0.0258 0.5702 0.0212
-1.500 -0.2048 0.00934 0.00210 0.0261 0.5564 0.0216
-1.250 -0.1818 0.00975 0.00202 0.0268 0.3971 0.0222
-1.000 -0.1561 0.00987 0.00200 0.0272 0.3486 0.0237
-0.500 -0.1054 0.00994 0.00192 0.0280 0.2692 0.0593
-0.250 -0.0786 0.00992 0.00190 0.0282 0.2603 0.0706
0.000 -0.0523 0.00984 0.00187 0.0285 0.2522 0.0913
0.250 -0.0369 0.00872 0.00161 0.0305 0.2453 0.3677
0.500 -0.0130 0.00846 0.00156 0.0312 0.2356 0.4309
0.750 0.0066 0.00793 0.00147 0.0326 0.2156 0.5645
1.000 0.0284 0.00816 0.00157 0.0336 0.1370 0.6143
1.250 0.0517 0.00836 0.00169 0.0344 0.0900 0.6455
1.500 0.0771 0.00837 0.00177 0.0349 0.0841 0.6720
1.750 0.1022 0.00835 0.00185 0.0355 0.0822 0.7020
2.000 0.1273 0.00834 0.00196 0.0361 0.0811 0.7316
2.250 0.1512 0.00831 0.00207 0.0370 0.0798 0.7682
2.500 0.1759 0.00834 0.00221 0.0377 0.0784 0.7966
2.750 0.2010 0.00841 0.00235 0.0383 0.0767 0.8169
3.000 0.2263 0.00853 0.00253 0.0389 0.0745 0.8343
3.250 0.2515 0.00867 0.00273 0.0395 0.0726 0.8526
3.500 0.2760 0.00887 0.00301 0.0402 0.0706 0.8733
3.750 0.3024 0.00892 0.00311 0.0405 0.0700 0.8911
4.000 0.3293 0.00900 0.00323 0.0407 0.0691 0.9046
4.250 0.3568 0.00912 0.00338 0.0408 0.0680 0.9168
4.500 0.3850 0.00926 0.00354 0.0407 0.0665 0.9277
4.750 0.4126 0.00941 0.00370 0.0407 0.0652 0.9385
5.000 0.4437 0.00959 0.00388 0.0399 0.0636 0.9465
5.250 0.4729 0.00982 0.00410 0.0395 0.0619 0.9548
5.500 0.5056 0.01020 0.00450 0.0383 0.0597 0.9605
5.750 0.5343 0.01022 0.00451 0.0381 0.0591 0.9679
6.000 0.5710 0.01030 0.00457 0.0361 0.0577 0.9701
6.250 0.6068 0.01040 0.00464 0.0343 0.0552 0.9723
6.500 0.6411 0.01057 0.00473 0.0327 0.0515 0.9747
6.750 0.6733 0.01076 0.00491 0.0316 0.0491 0.9778
7.000 0.7022 0.01097 0.00508 0.0312 0.0449 0.9818
7.250 0.7367 0.01133 0.00532 0.0294 0.0325 0.9831
7.500 0.7693 0.01195 0.00589 0.0278 0.0200 0.9851
7.750 0.8027 0.01234 0.00630 0.0263 0.0190 0.9872
8.000 0.8353 0.01269 0.00668 0.0250 0.0184 0.9897
8.250 0.8660 0.01306 0.00710 0.0240 0.0179 0.9923
8.500 0.8980 0.01348 0.00756 0.0227 0.0173 0.9941
8.750 0.9316 0.01390 0.00802 0.0211 0.0171 0.9957
9.000 0.9644 0.01439 0.00856 0.0195 0.0167 0.9975
9.250 0.9968 0.01494 0.00917 0.0180 0.0162 0.9992
9.500 1.0217 0.01553 0.00981 0.0179 0.0157 1.0000
9.750 1.0353 0.01610 0.01044 0.0201 0.0153 1.0000
10.000 1.0472 0.01678 0.01118 0.0226 0.0149 1.0000
10.250 1.0568 0.01759 0.01206 0.0253 0.0145 1.0000
10.500 1.0631 0.01859 0.01314 0.0285 0.0141 1.0000
10.750 1.0770 0.01907 0.01367 0.0306 0.0140 1.0000
11.000 1.0896 0.01962 0.01428 0.0328 0.0138 1.0000
11.250 1.1015 0.02021 0.01492 0.0350 0.0136 1.0000
11.500 1.1116 0.02090 0.01567 0.0374 0.0133 1.0000
11.750 1.1156 0.02159 0.01642 0.0408 0.0130 1.0000
12.000 1.1189 0.02239 0.01728 0.0440 0.0127 1.0000
12.250 1.1236 0.02336 0.01832 0.0463 0.0124 1.0000
12.500 1.1282 0.02457 0.01960 0.0481 0.0121 1.0000
12.750 1.1317 0.02604 0.02114 0.0495 0.0118 1.0000
13.000 1.1322 0.02792 0.02309 0.0505 0.0116 1.0000
13.250 1.1242 0.03066 0.02592 0.0514 0.0113 1.0000
13.500 1.1220 0.03308 0.02843 0.0520 0.0111 1.0000
13.750 1.1341 0.03427 0.02971 0.0521 0.0109 1.0000
14.000 1.1385 0.03620 0.03173 0.0522 0.0107 1.0000
14.250 1.1447 0.03804 0.03365 0.0523 0.0104 1.0000
14.500 1.1456 0.04041 0.03612 0.0522 0.0102 1.0000
14.750 1.1452 0.04299 0.03879 0.0519 0.0100 1.0000
15.000 1.1412 0.04609 0.04198 0.0513 0.0098 1.0000
15.250 1.1363 0.04941 0.04541 0.0504 0.0097 1.0000
15.500 1.1285 0.05337 0.04948 0.0490 0.0096 1.0000
15.750 1.1199 0.05794 0.05417 0.0469 0.0094 1.0000
16.000 1.1066 0.06432 0.06069 0.0431 0.0093 1.0000
16.250 1.0935 0.07099 0.06748 0.0391 0.0093 1.0000
16.500 1.0783 0.07781 0.07442 0.0352 0.0092 1.0000
16.750 1.0594 0.08483 0.08154 0.0316 0.0093 1.0000
17.000 1.0407 0.09183 0.08864 0.0280 0.0092 1.0000
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Polar data table (+)
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